U.S. patent number 3,636,335 [Application Number 05/060,305] was granted by the patent office on 1972-01-18 for turbine inlet temperature computer.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Robert E. Nelson, Robert K. Sanders, Oran Alton Watts, III.
United States Patent |
3,636,335 |
Nelson , et al. |
January 18, 1972 |
**Please see images for:
( Certificate of Correction ) ** |
TURBINE INLET TEMPERATURE COMPUTER
Abstract
The turbine expansion ratio is calculated by a
divider-multiplier circuit which divides a direct current
compressor discharge pressure signal of a magnitude proportional to
the compressor discharge pressure by a direct current turbine exit
pressure signal of a magnitude proportional to the turbine exit
pressure to produce a direct current turbine expansion ratio signal
of a magnitude proportional to the turbine expansion ratio. A curve
generator responsive to the turbine expansion ratio signal produces
the reciprocal of a K factor signal which is a function of the
turbine expansion ratio signal. A direct current mass fuel flow
signal of a magnitude proportional to the mass fuel flow is divided
by the compressor discharge pressure signal and the quotient
multiplied by the reciprocal of the K factor signal in a second
divider-multiplier circuit and a direct current burner inlet
temperature signal of a magnitude proportional to the burner inlet
temperature is added to this product to provide a direct current
signal of a magnitude proportional to the computed turbine inlet
temperature.
Inventors: |
Nelson; Robert E.
(Indianapolis, IN), Sanders; Robert K. (Whitestown, IN),
Watts, III; Oran Alton (Indianapolis, IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
26736188 |
Appl.
No.: |
05/060,305 |
Filed: |
August 3, 1970 |
Current U.S.
Class: |
702/130;
701/100 |
Current CPC
Class: |
G06G
7/64 (20130101); G06G 7/161 (20130101); G06G
7/28 (20130101); F01D 17/085 (20130101) |
Current International
Class: |
G06G
7/161 (20060101); G06G 7/00 (20060101); F01D
17/00 (20060101); F01D 17/08 (20060101); G06G
7/64 (20060101); G06G 7/28 (20060101); G06g
007/16 (); G06g 007/57 () |
Field of
Search: |
;235/193,194,195,196,151.3,151.34,197 ;207/229 ;328/160,161 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Ruggiero; Joseph F.
Claims
What is claimed is:
1. A turbine inlet temperature computer for computing the turbine
inlet temperature of a gas turbine-type engine having at least a
compressor stage, a burner stage and a turbine stage on the basis
of the compressor discharge pressure, the turbine exit pressure,
the mass fuel flow and the burner inlet temperature comprising:
means for producing a compressor discharge pressure direct current
potential signal of a magnitude proportional to the discharge
pressure of said compressor stage, means for producing a turbine
exit pressure direct current potential signal of a magnitude
proportional to the exit pressure of said turbine stage, means
responsive to said compressor discharge pressure signal and said
turbine exit pressure signal for producing a turbine expansion
ratio direct current potential output signal of a magnitude
proportional to the expansion ratio of said turbine stage, means
responsive to said turbine expansion ratio signal for producing a
direct current potential signal which is the reciprocal of said
turbine K factor, means for producing a mass fuel flow direct
current potential signal of a magnitude proportional to the mass
fuel flow to said turbine engine, means for producing a burner
inlet temperature direct current potential signal of a magnitude
proportional to the inlet temperature of said burner stage, means
for dividing said mass fuel flow signal by said compressor
discharge pressure signal, means for multiplying the quotient of
said mass fuel flow signal divided by said compressor discharge
pressure signal by said reciprocal of said turbine K factor signal,
and means for adding said burner inlet temperature signal to the
product of the quotient of said mass fuel flow signal divided by
said compressor discharge pressure signal multiplied by said
reciprocal of said turbine K factor signal.
2. A turbine inlet temperature computer for computing the turbine
inlet temperature of a gas turbine-type engine having at least a
compressor stage, a burner stage and a turbine stage on the basis
of the compressor discharge pressure, the turbine exit pressure,
the mass fuel flow and the burner inlet temperature comprising:
means for producing a compressor discharge pressure direct current
potential signal of a magnitude proportional to the discharge
pressure of said compressor stage, means for producing a turbine
exit pressure direct current potential signal of a magnitude
proportional to the exit pressure of said turbine stage, means for
dividing said compressor discharge pressure signal by said turbine
exit pressure signal for producing a turbine expansion ratio direct
current potential output signal of a magnitude proportional to the
expansion ratio of said turbine stage, means responsive to said
turbine expansion ratio signal for producing a direct current
potential signal which is the reciprocal of said turbine K factor,
means for producing a mass fuel flow direct current potential
signal of a magnitude proportional to the mass fuel flow to said
turbine engine, means for producing a burner inlet temperature
direct current potential signal of a magnitude proportional to the
inlet temperature of said burner stage, means for dividing said
mass fuel flow signal by said compressor discharge pressure signal,
means for multiplying the quotient of said mass fuel flow signal
divided by said compressor discharge pressure signal by said
reciprocal of said turbine K factor signal, and means for adding
said burner inlet temperature signal to the product of the quotient
of said mass fuel flow signal divided by said compressor discharge
pressure signal multiplied by said reciprocal of said turbine K
factor signal.
3. A turbine inlet temperature computer for computing the turbine
inlet temperature of a gas turbine-type engine having at least a
compressor stage, a burner state and a turbine stage on the basis
of the compressor discharge pressure, the turbine exit pressure,
the mass fuel flow and the burner inlet temperature comprising:
means for producing a compressor discharge pressure direct current
potential signal of a magnitude proportional to the discharge
pressure of said compressor stage, means for producing a turbine
exit pressure direct current potential signal of a magnitude
proportional to the exit pressure of said turbine stage, means
responsive to said compressor discharge pressure signal and said
turbine exit pressure signal for producing a turbine expansion
ratio direct current potential output signal of a magnitude
proportional to the expansion ratio of said turbine stage, means
responsive to said turbine stage, means responsive to said turbine
expansion ratio signal for producing a direct current potential
signal which is the reciprocal of said turbine K factor, means for
producing a mass fuel flow direct current potential signal of a
magnitude proportional to the mass fuel flow to said turbine
engine, means for producing a burner inlet temperature direct
current potential signal of a magnitude proportional to the inlet
temperature of said burner stage, a divider-multiplier circuit of
the type capable of dividing the dividend direct current potential
signal by a divisor direct current potential signal and multiplying
the quotient by a multiplier direct current potential signal having
at least a respective input circuit for each the dividend, divisor
and multiplier electric signals and a direct current potential
summing input circuit for producing the turbine inlet temperature
direct current potential output signal which is the quotient of
said mass fuel flow signal divided by said compressor discharge
pressure signal multiplied by said reciprocal of said turbine K
factor signal plus said burner inlet temperature signal, means for
applying said mass fuel flow signal to said dividend input circuit
of said second divider-multiplier circuit, means for applying said
compressor discharge pressure signal to said divisor input circuit
of said second divider-multiplier circuit, means for applying said
reciprocal of said turbine K factor signal to said multiplier input
circuit of said second divider-multiplier circuit, and means for
applying said burner inlet temperature signal to said summing input
circuit of said second divider-multiplier circuit.
4. A turbine inlet temperature computer for computing the turbine
inlet temperature of a gas turbine-type engine having at least a
compressor stage, a burner stage and a turbine stage on the basis
of the compressor discharge pressure, the turbine exit pressure,
the mass fuel flow and the burner inlet temperature comprising:
means for producing a compressor discharge pressure direct current
potential signal of a magnitude proportional to the discharge
pressure of said compressor stage, means for producing a turbine
exit pressure direct current potential signal of a magnitude
proportional to the exit pressure of said turbine stage, means for
producing a constant direct current potential signal of a selected
magnitude, a first divider-multiplier circuit of the type capable
of dividing a dividend direct current potential signal by a divisor
direct current potential signal and multiplying the quotient by a
multiplier direct current potential signal having at least a
respective input circuit for each the dividend, divisor and
multiplier input signals for producing a turbine expansion ratio
direct current potential output signal of a magnitude proportional
to the expansion ratio of said turbine stage, means for applying
said compressor discharge pressure signal to said dividend input
circuit of said first divider-multiplier circuit, means for
applying said turbine exit pressure signal to said divisor input
circuit of said first divider-multiplier circuit, means for
applying said constant direct current potential signal to said
multiplier input circuit of said first divider-multiplier circuit,
a curve generator responsive to said turbine expansion ratio signal
for producing a direct current potential output signal which is the
reciprocal of the turbine K factor, means for applying said turbine
expansion ratio output signal from said first divider-multiplier
circuit to said curve generator, means for producing a mass fuel
flow direct current potential signal of a magnitude proportional to
the weight of fuel flow to said turbine engine, means for producing
a burner inlet temperature direct current potential signal of a
magnitude proportional to the inlet temperature of said burner
stage, a second divider-multiplier circuit of the type capable of
dividing a dividend direct current potential signal by a divisor
direct current potential signal and multiplying the quotient by a
multiplier direct current potential signal having at least a
respective input circuit for each the dividend, divisor and
multiplier input signals and a direct current potential signal
summing input circuit for producing the turbine inlet temperature
direct current potential output signal which is the quotient of
said mass fuel flow signal divided by said compressor discharge
pressure signal multiplied by the reciprocal of said turbine K
factor signal plus said burner inlet temperature signal, means for
applying said mass fuel flow signal to said dividend input circuit
of said second divider-multiplier circuit, means for applying said
compressor discharge pressure signal to said divisor input circuit
of said second divider-multiplier circuit, means for applying said
curve generator output signal to said multiplier input circuit of
said second divider-multiplier circuit, and means for applying said
burner inlet temperature signal to said summing input circuit of
said second divider-multiplier circuit.
Description
The invention herein described was made in the course of work under
contract or subcontract thereunder with the Department of
Defense.
This invention is directed to a turbine inlet temperature computer
and, more specifically, to a turbine inlet temperature computer
which computes the turbine inlet temperature of a gas turbine-type
engine on the basis of the compressor discharge pressure, the
turbine exit pressure, the mass fuel flow and the burner inlet
temperature.
Because of the extremely high turbine inlet temperatures proposed
and being considered for further turbine type engines, the
capability of thermocouple designs, even with the use of rare and
noble metals, may be exceeded. Consequently, it is imperative that
the turbine inlet temperature be synthesized from readily
obtainable engine operating parameters which do not require
thermocouples or other types of probes in the high temperature
combustion gases of turbine-type engines.
It has been found that the inlet temperature of the turbine stage
of a gas turbine type engine may be accurately calculated on the
basis of compressor discharge pressure, turbine exit pressure, mass
fuel flow and burner inlet temperature. Therefore, the turbine
inlet temperature computer of this invention has been designed to
solve the following equation:
Tit = bit + c(wf/CDP) .times. (1/K) where:
Tit = turbine Inlet Temperature
Bit = burner Inlet Temperature
Cdp = compressor Discharge Pressure
Wf = Mass Fuel Flow
C = Engine Constant
K = Engine Airflow Factor described below
This equation is valid provided no air is bled from the turbine
after the compressor discharge pressure is measured or, in the
event of an air bleed off, the amount is known.
The factor K in this equation is an expression of the flow of air
through the turbine and may be determined for each turbine through
tests. The value of the K factor is minimum at starting or low
engine speeds and increases with engine speed until the value is
unity while the turbine is operating in a choked condition.
It is, therefore, an object of this invention to provide an
improved turbine inlet temperature computer.
It is another object of this invention to provide an improved
turbine inlet temperature computer which eliminates the necessity
of thermocouples or other types of probes in the high temperature
combustion gases of turbine-type engines.
It is a further object of this invention to provide an improved
turbine inlet temperature computer for computing the turbine inlet
temperature of a gas turbine-type engine on the basis of readily
obtainable engine operating parameters such as compressor discharge
pressure, turbine exit pressure, mass fuel flow and burner inlet
temperature.
In accordance with this invention, a turbine inlet temperature
computer for computing the turbine inlet temperature of a gas
turbine type engine on the basis of respective direct current
electrical signals of a magnitude proportional to compressor
discharge pressure, turbine exit pressure, mass fuel flow and
burner inlet temperature is provided wherein the turbine expansion
ratio is calculated by a divider-multiplier circuit in which the
compressor discharge pressure electrical signal is divided by the
turbine exit pressure electrical signal to produce a direct current
signal which is the analog representation of the turbine expansion
ratio, the mass fuel flow electrical signal is divided by the
compressor discharge pressure electrical signal and the quotient is
multiplied by the reciprocal of a K factor signal, which is a
function of the turbine expansion ratio direct current signal, in
another divider-multiplier circuit and the burner inlet temperature
signal is added to this product to provide a computed turbine inlet
temperature potential signal.
For a better understanding of the present invention, together with
additional objects, advantages and features thereof, reference is
made to the following description and accompanying drawings in
which:
FIG. 1 is a block form diagram of the turbine inlet temperature
computer of this invention;
FIG. 2 is a schematic diagram of a divider-multiplier circuit
suitable for use with the turbine inlet temperature computer of
this invention;
FIG. 3 is a schematic diagram of a reference signal source suitable
for use with the divider-multiplier circuit of FIG. 2;
FIG. 4 illustrates a direct current operating potential source
suitable for use with the turbine inlet temperature computer of
this invention;
FIG. 5 is a curve showing a typical turbine expansion ratio vs. K
factor relationship;
FIG. 6 is a set of curves useful in understanding the description
of the divider-multiplier circuits used in the turbine inlet
temperature computer of this invention; and
FIG. 7 is a schematic diagram, partially in block form, of a curve
generator suitable for use with the turbine inlet temperature
computer of this invention.
In FIGS. 1, 2, 3, 4 and 7 of the drawings, the point of reference
or ground potential has been represented by the accepted schematic
symbol and referenced by the numeral 5.
As has been hereinbefore brought out, the K factor of a turbine is
an expression of airflow therethrough and may be determined by
proper tests. The relationship between the K factor and turbine
expansion ratio of a typical turbine is shown by the curve of FIG.
5. As the K factor is a function of the turbine expansion ratio,
this term of the equation, hereinabove set forth, which is
calculated by the turbine inlet temperature computer of this
invention is obtained by calculating the turbine expansion ratio
which is the compressor discharge pressure divided by the turbine
exit pressure.
The direct current operating potential source is indicated in FIG.
4 to be a battery 9 having positive and negative polarity output
terminals with respect to point of reference or ground potential 5.
It is to be specifically understood, however, that any conventional
direct current potential source having equal magnitude output
potentials of a positive and a negative polarity with respect to
point of reference or ground potential may be employed without
departing from the spirit of the invention.
To reduce the complexity of FIGS. 1, 2, 3 and 7 of the drawings,
the circuit connections to the direct current operating potential
source 9 have not been shown. However, all points of the circuits
of the FIGURES which are connected to the positive polarity output
terminal of direct current operating potential source 9 are labeled
+ V and all points of the circuits of these FIGURES which are
connected to the negative polarity output terminal of direct
current operating potential source 9 are labeled - V.
Referring to FIG. 1 of the drawings, the turbine inlet temperature
computer of this invention for computing the turbine inlet
temperature of a gas turbine-type engine having at least a
compressor stage, a burner stage and a turbine stage on the basis
of the compressor discharge pressure, the turbine exit pressure,
the mass fuel flow and the burner inlet temperature is set forth in
block form and comprises a pressure transducer 10 for producing a
compressor discharge pressure direct current potential signal of a
magnitude proportional to the discharge pressure of the compressor
stage; a pressure transducer 11 for producing a turbine exit
pressure direct current potential signal of a magnitude
proportional to the exit pressure of the turbine stage; circuitry
responsive to the compressor discharge pressure signal and the
turbine exit pressure signal for producing a turbine expansion
ratio direct current potential output signal of a magnitude
proportional to the expansion ratio of the turbine stage, may be a
combined divider-multiplier circuit 20; circuitry responsive to the
turbine expansion ratio signal for producing a direct current
potential signal which is the reciprocal of the turbine K factor,
may be a curve generator 26; circuitry for producing a mass fuel
flow direct current potential signal of a magnitude proportional to
the mass fuel flow to the turbine engine, may be a fuel flow meter
12, circuitry for producing a burner inlet temperature direct
current potential signal of a magnitude proportional to the inlet
temperature of the burner stage, may be a temperature-sensitive
variable resistor 13 and the associated circuitry; circuitry for
dividing the mass fuel flow signal by the compressor discharge
pressure signal; circuitry for multiplying the quotient of the mass
fuel flow signal divided by the compressor discharge pressure
signal by the reciprocal of the engine K factor potential signal
and circuitry for adding the burner inlet temperature signal to the
product of the quotient of the mass fuel flow signal divided by the
compressor discharge pressure signal multiplied by the reciprocal
of the engine K factor signal.
Without intention or inference of a limitation thereto, the divide
and multiply circuits which calculate the turbine inlet temperature
may be combined in a divider-multiplier circuit 40 of the type
capable of dividing a dividend direct current potential signal by a
divisor direct current potential signal and multiplying the
quotient by a multiplier direct current potential signal having at
least a respective input circuit for each the dividend, divisor,
and multiplier electrical signals and a direct current potential
signal summing input circuit for producing the turbine inlet
temperature direct current potential output signal which is the
quotient of the mass fuel flow signal divided by the compressor
discharge pressure signal multiplied by the reciprocal of the
engine K factor signal plus the burner inlet temperature
signal.
To produce the direct current potential signal of a magnitude
proportional to the discharge pressure of the compressor stage,
hereinafter termed the compressor discharge pressure signal, and
the direct current potential signal of a magnitude proportional to
the exit pressure of the turbine stage, hereinafter termed the
turbine exit pressure signal, pressure transducers of the type
sensitive to static pressures for producing a direct current
potential output signal proportional thereto may be employed for
the compressor discharge pressure transducer 10 and the turbine
exit pressure transducer 11. Instruments of this type, suitable for
use with the turbine inlet temperature computer of this invention,
are commercially available from Servonic Instruments, Inc. of
Willow Grove, Pa. and Costa Nasa, Calif. The important
characteristics of these transducers is the ability to accurately
sense static pressure. These transducers are located at the
discharge of the compressor and the turbine, respectively, in a
manner well known in the art and each is schematically illustrated
in FIG. 1 as four variable resistors connected in a bridge
configuration having one pair of diagonal junctions connected
across the positive polarity output terminal of direct current
operating potential source 9 and point of reference or ground
potential 5.
To produce a direct current potential signal of a magnitude
proportional to the mass fuel flow to the turbine engine,
hereinafter termed the weight of fuel flow signal, a real mass flow
meter of the type which produces a direct current potential output
signal of a magnitude proportional to the mass fuel flow may be
employed in the line which supplies fuel to the turbine. Flow
meters of this type are commercially available from the General
Electric Company.
The turbine exit pressure signal, the compressor discharge pressure
signal and the mass fuel flow signal may be amplified by respective
amplifiers 14, 16 and 18, each having an output terminal 15, 17 and
19, respectively. As these amplifiers may be commercially available
operational amplifiers or any other type direct current amplifier
well known in the art and, per se, forms no part of this invention,
each has been indicated in block form in FIG. 1.
To produce a direct current potential signal of a magnitude
proportional to the inlet temperature of the burner stage,
hereinafter termed the burner inlet temperature signal, a platinum
wire 13 may be located in the input of the burner stage in a manner
well known in the art. This platinum wire may be energized by a
constant direct current through a constant current circuit. A
satisfactory constant current circuit may be in the form of a type
PNP-transistor 30 having the usual base electrode 31, emitter
electrode 32 and collector electrode 33. As is well known in the
art, with a constant base-emitter bias potential applied to a
transistor, the emitter-collector current flow therethrough remains
substantially constant regardless of changes in supply potential.
The emitter electrode 32 of transistor 30 is connected to the
positive polarity output terminal of direct current operating
potential source 9 through emitter resistor 34 and the collector
electrode 33 is connected through the temperature sensitive
resistor 13, which may be a platinum wire, in series to point of
reference or ground potential 5. Consequently, the
emitter-collector electrodes of type PNP-transistor 30 are properly
poled for forward emitter-collector conduction therethrough. The
base electrode 31 of transistor 30 is connected to junction 35
between series resistors 36 and 37 connected across the positive
polarity terminal of direct current operating potential source 9
and point of reference or ground potential 5. With this
arrangement, a substantially constant direct current bias potential
is applied across the emitter-base electrodes of type
PNP-transistor 30 in the proper polarity relationship to produce
emitter-base current flow through a type PNP-transistor.
Consequently, a substantially constant emitter-collector current
flows through type PNP-transistor 30. As temperature sensitive
resistor 13 is supplied from a constant current source, any change
of current therethrough will be the result of a change in ambient
temperature.
The circuitry responsive to the compressor discharge pressure
signal and the turbine exit pressure signal for producing a turbine
expansion ratio direct current potential output signal of a
magnitude proportional to the expansion ratio of the turbine stage
may be a divider-multiplier circuit 20 of a type identical to
divider-multiplier circuit 40 wherein the compressor discharge
pressure signal is divided by the turbine exit pressure signal.
Without intention or inference of a limitation thereto, one example
of a divider-multiplier circuit suitable for use as
divider-multiplier circuits 20 and 40 of the turbine inlet
temperature computer of this invention is disclosed and described
in detail in copending U.S. Pat. application, Ser. No. 57,202,
filed July 22, 1970, and assigned to the same assignee as is this
application and is set forth schematically in FIG. 2.
Although the operation of the turbine inlet temperature computer of
this invention will be described on the basis of the
divider-multiplier circuit schematically set forth in FIG. 2, it is
to be specifically understood that alternate circuits may be used
to perform the arithmetic operations performed by these circuits
without departing from the spirit of the invention.
The divider-multiplier circuit of FIG. 2 is operated by an
alternating current, square waveform reference signal source having
two complementary polarity output circuits. One example of a square
waveform alternating current reference signal source suitable for
use with the divider-multiplier circuit of FIG. 2 is schematically
set forth in FIG. 3. This reference signal source may be a
conventional astable or free-running multivibrator circuit
including two type NPN-transistors 60 and 70 and the associated
circuitry. Upon the application of the operating potential to this
circuit, a forward base-emitter potential is applied across the
base-emitter electrodes of both transistors 60 and 70 in the proper
polarity relationship to produce base-emitter current flow through
type NPN transistors. As the circuit parameters are not precisely
equal, one of the other of transistors 60 or 70 will initially
conduct through the collector-emitter electrodes thereof. For
purposes of this specification, it will be assumed that transistor
60 initially conducts through the collector-emitter electrodes.
Upon the conduction of transistor 60, the base electrode 71 of
transistor 70 is connected to the negative polarity output terminal
of battery 9 through capacitor 72 and diode 73, a condition which
maintains transistor 70 not conductive, and capacitor 72 charges
through a circuit which may be traced from the positive polarity
output terminal of battery 9 through collector resistor 74, diode
75, resistor 76, capacitor 72, diode 73 and the collector-emitter
electrodes of conducting transistor 60 to the negative polarity
terminal of battery 9. When capacitor 72 has become charged, the
potential upon junction 77 goes positive of a sufficient magnitude
to produce base-emitter current flow through type NPN-transistor 70
to initiate collector-emitter current flow therethrough. Upon the
conduction of transistor 70, the base electrode 61 of transistor 60
is connected to the negative polarity output terminal of battery 9
through capacitor 62 and diode 63, a condition which extinguishes
transistor 60 and capacitor 62 charges through a circuit which may
be traced from the positive polarity output terminal of battery 9,
through collector resistor 64, diode 65, resistor 66, capacitor 62,
diode 63 and the collector-emitter electrodes of conducting
transistor 70 to the negative polarity terminal of battery 9. When
capacitor 62 has become charged, the potential upon junction 67
goes positive of a sufficient magnitude to produce base-emitter
current flow through type NPN-transistor 60 to initiate
collector-emitter current flow therethrough. Upon the conduction of
transistor 60, the base electrode 71 of transistor 70 is again
connected to the negative polarity output terminal of battery 9
through the circuit previously described, consequently, transistor
70 extinguishes and capacitor 72 again begins to charge through the
circuit previously described. This action continues with
transistors 60 and 70 alternately conducting at a frequency
determined by the values of resistors 74 and 76 and capacitor 72
and resistors 64 and 66 and capacitor 62. The output signals may be
taken from the collector of respective transistors 60 and 70
through respective output terminals 68 and 69. While transistor 70
is conducting, a positive polarity output signal, with respect to
point of reference or ground potential 5, is present upon output
circuit terminal 68 and a negative polarity output signal, with
respect to point of reference or ground potential 5, is present
upon output circuit terminal 69. While transistor 60 is conducting,
a negative polarity output signal, with respect to point of
reference or ground potential 5, is present upon output circuit
terminal 68 and a positive polarity output signal, with respect to
point of reference or ground potential 5, is present upon output
circuit terminal 69. These signals are graphically illustrated as
curve A of FIG. 6. Consequently, this circuit provides a square
waveform alternating current reference signal source having two
complementary polarity output circuits. In a practical application
of the circuit of this invention, the square waveform alternating
current reference signal source had a frequency of 2
kilocycles.
The divider-multiplier circuits 20 and 40 of FIG. 1 are set forth
schematically in FIG. 2 and have at least a respective input
circuit for each the dividend, divisor and multiplier input signals
which may be respective terminals 21, 22, and 23 and a summing
input circuit which may be a terminal 24. It is to be specifically
understood that terminals 21 through 24 may be any electrical
device suitable for connection to external circuitry. Each
divider-multiplier circuit also includes an operational amplifier
42 having an inverting input terminal 43, an output terminal 44 and
a feedback capacitor 41, an operational amplifier 45 having an
inverting input terminal 46, an output terminal 47 and a feedback
capacitor 48 and resistor 49 and an operational amplifier 50 having
an inverting input terminal 51 and an output terminal 52.
Operational amplifiers are high gain, direct current amplifiers,
which are well known in the art and are commercially available,
having an inverting input circuit, a noninverting input circuit and
an output circuit. An input signal applied to the inverting input
circuit of an operational amplifier produces an output signal of
the opposite polarity and an input signal applied to the
noninverting input circuit produces an output signal of the same
polarity.
As is well known in the art, operational amplifiers may be
converted to direct current signal integrating circuits by
providing a feedback capacitor between the output circuit and the
inverting input circuit. Consequently, operational amplifier 42
functions as a direct current signal integrating circuit.
Operational amplifier 45 operates as a direct current signal
averaging circuit which produces an output signal of a magnitude
proportional to the magnitudes of a series of direct current pulses
applied to the inverting input circuit 46.
Operational amplifier 50, to the inverting input terminal 51 of
which output terminal 44 of integrating operational amplifier 42 is
connected, is operated in the open loop mode and functions as a
sensitive direct current switch. Operational amplifier 50 produces
an output signal of a negative polarity when the output signal of
integrating operational amplifier 42 is of a positive polarity and
an output signal of a positive polarity when the output signal of
integrating operational amplifier 42 is of a negative polarity.
The source-drain electrodes of respective field effect transistors
53 and 54 are connected between input terminals 21 and 22 and the
inverting input terminal 43 of integrating operational amplifier 42
and the source-drain electrodes of field effect transistor 55 are
connected between input terminal 23 and inverting input terminal 46
of averaging operational amplifier 45. Each of these field effect
transistors is of the N-channel type which is normally conductive
through the source-drain electrodes unless maintained not
conductive by a negative polarity signal upon the gate electrode
thereof. Field effect transistors 53, 54 and 55 function as
potential sensitive switches to apply the input signals to the
divider-multiplier circuit in the proper sequence. Consequently,
output terminal 68 of the source of reference signals of FIG. 3 is
connected to the gate electrode of field effect transistor 53
through input terminal 78 through a lead (not shown)
interconnecting these two terminals and output terminal 69 of the
reference signal source of FIG. 3 is connected to the gate
electrode of each of field effect transistors 54 and 55 through
input terminal 79 through a lead (not shown) interconnecting these
two terminals.
For purposes of this specification, and without intention or
inference of a limitation thereto, it will be assumed that the
amplified compressor discharge pressure signal, the amplified
turbine exit pressure signal and the burner inlet temperature
signal are of a positive polarity and the amplified mass fuel flow
signal is of a negative polarity.
The positive polarity compressor discharge pressure signal is
applied through amplifier 16 and a signal inverter 58 to the
dividend input terminal 21 of divider-amplifier 20 through a lead
38 connecting output terminal 59 of signal inverter 58 to dividend
input terminal 21 of divider-multiplier 20.
The positive polarity turbine exit pressure signal is applied
through amplifier 14 to the divisor input terminal 22 of
divider-multiplier 20 through a lead 39 connecting output terminal
15 of amplifier 14 to divisor input terminal 22 of
divider-multiplier 20.
Input terminal 24 of divider-multiplier 20 is not utilized in
divider-multiplier 20.
As signal inverter 58 may be any conventional inverter circuit well
known in the art and forms no part of this invention, it has been
indicated in block form in FIG. 1.
Divider-multiplier circuit 20 calculates the turbine expansion
ratio by dividing the compressor discharge pressure signal by the
turbine exit pressure signal. As this divider-multiplier circuit
requires a multiplier input signal to produce an output, the
quotient of the compressor discharge pressure signal and the
turbine exit pressure signal is multiplied by a preselected
constant direct current potential signal which may be obtained from
the negative polarity output terminal of direct current operating
potential source 9.
Over those half cycles of the alternating current reference signals
during which output terminals 68 and 69 of the reference signal
source of FIG. 3 are of a positive and a negative polarity,
respectively, with respect to point of reference or ground
potential 5, the positive polarity signal upon output terminal 68,
applied to the gate electrode of field effect transistor 53,
permits this device to conduct, and the negative polarity signal
upon output terminal 69, applied to the gate electrodes of field
effect transistors 54, 55 and 56, holds these devices not
conductive. While field effect transistor 53 conducts, the inverted
compressor discharge pressure signal appears across load resistor
90, curve B of FIG. 6. The negative polarity inverted compressor
discharge pressure signal, therefore, is applied to the inverting
input circuit terminal 43 of integrating operational amplifier 42
which integrates this negative polarity dividend signal in a
positive direction for the duration of these half cycles of the
reference signals, as shown in curve D of FIG. 6. As the output
signal upon output circuit terminal 44 of integrating operational
amplifier 42 is of a positive polarity, the output signal upon
output circuit terminal 52 of operational amplifier 50 is of a
negative polarity. With a negative polarity signal present upon the
output circuit 52 of operational amplifier 50, type NPN-transistor
100 is not conductive. Consequently, the potential upon junction 95
is of a positive polarity. This signal is of no effect at this time
as the negative polarity reference signal maintains field effect
transistor 55 not conductive.
Over the alternate half cycles of the alternating current reference
signals during which output terminals 68 and 69 of the reference
signal source of FIG. 3 are of a negative and a positive polarity,
respectively, with respect to point of reference or ground
potential 5, the negative polarity output signal upon output
terminal 68 extinguishes field effect transistor 53 to remove the
compressor discharge pressure signal from integrating operational
amplifier 42 and the positive polarity signal upon output terminal
69 permits field effect transistors 54 and 55 to conduct. Although
this signal is also applied to the gate electrode of reset field
effect transistor 56, this device is maintained not conductive by
the negative polarity signal present upon output circuit terminal
52 of operational amplifier 50 which is applied to the gate
electrode thereof. While field effect transistors 54 and 55
conduct, the positive polarity turbine exit pressure signal appears
across load resistor 91, curve C of FIG. 6 and, simultaneously, the
constant negative polarity multiplier signal appears across load
resistor 92, curve E of FIG. 6. The positive polarity turbine exit
pressure signal, therefore, is applied to the inverting input
circuit terminal 43 of integrating operational amplifier 42 which
integrates this positive polarity divisor signal in a negative
polarity direction, as shown in curve D of FIG. 6.
When integrating operational amplifier 42 has integrated the
turbine exit pressure signal to substantially zero, operational
amplifier 50 switches to its alternate state in which the output
signal is of a positive polarity. This positive polarity signal
produces base-emitter current flow through type NPN-transistor 100
to initiate collector-emitter current flow therethrough. Upon the
conduction of transistor 100 through the collector-emitter
electrodes, the potential upon junction 95 goes negative and is
applied to the gate electrode of field effect transistor 55 to
extinguish field effect transistor 55 which disconnects the
constant multiplier signal from the averaging circuit.
Simultaneously, the positive polarity signal upon output circuit
terminal 52 of operational amplifier 50 permits source-drain
current flow through reset field effect transistor 56, a condition
which resets the output signal upon output circuit terminal 44 of
integrating operational amplifier 42 to zero.
The magnitude of the dividend signal determines the magnitude of
the integrated dividend signal and the magnitude of the divisor
signal determines the length of time required for integrating
operational amplifier 42 to integrate the divisor signal in the
opposite direction to substantially zero. Consequently, the length
of time required for integrating operational amplifier 42 to
integrate the divisor signal to substantially zero is a function of
the ratio of the relative magnitudes of the divisor signal and the
dividend signal and is an analog representation of the quotient of
the dividend signal divided by the divisor signal. For example, as
the dividend signal is integrated in a first direction by
integrating operational amplifier 42 for the duration of a complete
half cycle of the reference signals, the length of time required
for integrating operational amplifier 42 to integrate a divisor
signal of a magnitude precisely equal to the magnitude of the
dividend signal to substantially zero is equal to the period of a
complete half cycle of the reference signals, or unity, and to
integrate a divisor signal of a magnitude precisely equal to twice
the magnitude of the dividend signal to substantially zero is equal
to the period of one-fourth cycle of the reference signals, or 0.5.
As the multiplier signal appears across load resistor 92 for the
period of time required for integrating operational amplifier 42 to
integrate the divisor signal to substantially zero, the width of
the multiplier signal pulse across load resistor 92 is also an
analog representation of the quotient of the dividend signal
divided by the divisor signal. Consequently, the multiplier signal
appears across load resistor 92 as a series of direct current
pulses of a magnitude equal to the magnitude of the multiplier
signal and for a duration of time which is the analog
representation of the quotient of the dividend signal divided by
the divisor signal. These direct current pulses are averaged by
operational amplifier 45 and appear as a direct current potential
signal across output terminals 98 and 99 which represents, in
analog form, the product of the multiplier signal and the quotient
of the dividend signal divided by the divisor signal. The output
signal of averaging operational amplifier 45, therefore, is a
direct current potential signal of a magnitude proportional to the
turbine expansion ration.
The curve of FIG. 5 illustrates the relationship between the
turbine expansion ratio and the K factor of a typical turbine
engine which may be determined by test. Consequently, the turbine
expansion ratio-K relationship for any given engine may be
determined and a curve generator may be designed which will produce
an electrical signal corresponding to the reciprocal of the K
factor in response to the turbine expansion ratio signal present
upon the output circuit terminal 98 of divider-multiplier 20. The
output signal from divider-multiplier 20 is applied to the input
circuit of curve generator 26 through lead 93 which connects output
terminal 98 of divider-multiplier 20 to the input circuit of curve
generator 26. Curve generator 26 may be any one of the many curve
generators well known in the art of the type which provides an
output signal which is a nonlinear function of an input signal. One
example of a curve generator which may be used with the computer
circuit of this invention is set forth partially in schematic and
partially in block form in FIG. 7.
The curve generator of FIG. 7 includes three operational amplifiers
125, 135 and 145. The inverting input circuit terminal 126 and the
noninverting input circuit terminal 127 of operational amplifier
125 are connected to point of reference or ground potential 5
through respective resistors 130 and 131 and output circuit
terminal 128 is connected to the inverting input circuit terminal
126 through feedback resistor 129. Consequently, in the absence of
an input signal, the output of operational amplifier 125 is zero,
as shown by the curve adjacent the output thereof. The inverting
input circuit terminal 136 of operational amplifier 135 is
connected to junction 140 between series resistors 141 and 142
which are connected across the negative polarity output terminal of
direct current operating potential source 9 and point of reference
or ground potential 5, the non-inverting input circuit terminal 137
is connected to point of reference or ground potential 5 through
resistor 143 and the output circuit terminal is connected to the
inverting input circuit terminal 136 through a diode 144 and a
feedback resistor 139. Consequently, in the absence of an input
signal, the output of operational amplifier 135 is of a positive
polarity and of a magnitude determined by the potential drop across
resistor 142, as is shown by the curve adjacent the output circuit
thereof. The inverting input circuit terminal 146 of operational
amplifier 145 is connected to junction 150 between series resistors
151 and 152 connected across the negative polarity output terminal
of direct current operating potential source 9 and point of
reference or ground potential 5, the noninverting input circuit
terminal 147 is connected to point of reference or ground potential
5 through resistor 155 and the output circuit terminal 148 is
connected to the inverting input circuit terminal 146 through the
movable contact 157 of potentiometer 158 and feedback resistor 149.
Consequently, in the absence of an input signal, the output of
operational amplifier 145 is of a positive polarity and of a
magnitude determined by the potential drop across resistor 151, as
is shown by the curve adjacent the output circuit thereof. The
positive polarity turbine expansion ratio signal is applied to the
noninverting input circuit terminal 127 of operational amplifier
125 through input resistor 132 and to the inverting input circuit
terminal 136 of operational amplifier 135 through input resistor
134. Resistors 129 and 132 are proportioned to provide a high gain
for operational amplifier 125 and resistors 139 and 134 are
proportioned to provide a gain for operational amplifier 135 of a
degree less than the gain of operational amplifier 125. Therefore,
as the positive polarity turbine expansion ratio signal increases
in magnitude with an increase of turbine speed, the output of
operational amplifier rises steeply in a positive polarity
direction until operational amplifier 125 saturates, after which
the output signal remains substantially constant, as is shown in
the curve adjacent the output thereof, and the output signal of
operational amplifier 135 decreases in a negative polarity
direction at a rate slower than the increase of the output of
operational amplifier 125 until the output reaches zero, as shown
by the curve adjacent the output thereof. Diode 144, which becomes
reverse biased when the output circuit terminal 138 of operational
amplifier 135 goes negative, prevents the output signal appearing
across load resistor 160 from going below zero or negative. As the
output signal of operational amplifier 125 is applied to the
inverting input circuit terminal 146 of operational amplifier 145
through input resistor 153 and the output of operational amplifier
135 is also applied to the inverting input circuit terminal 146 of
operational amplifier 145 through input resistor 154, the rapidly
increasing output of operational amplifier 125 in a positive
polarity direction results in an output signal from operational
amplifier 145 which rapidly decreases in a negative polarity
direction, as shown in the curve adjacent the output thereof, until
operational amplifier 125 substantially saturates. At this time,
the negative going output potential from operational amplifier 135
becomes the dominant factor influencing the output signal from
operational amplifier 145. As this signal is decreasing in a
negative direction, the output of operational amplifier 145
decreases in a negative direction at a much slower rate to provide
the knee of the curve of the output signal of operational amplifier
145. When the output signal from operational amplifier 135 has
reached zero, the input signal to operational amplifier 145 no
longer changes and the output signal therefrom remains
substantially constant. Consequently, the output signal from curve
generator 26 closely approximates the reciprocal of the engine
turbine expansion ratio-K factor curve shown in FIG. 5. The level
of the constant portion of this curve is determined by adjusting
movable contact 157 of potentiometer 158, an operation which
operates to provide a signal for the constant C term of the
equation hereinabove set forth. For any given engine for which the
turbine expansion ratio-K factor relationship is known, resistors
129 and 132 of operational amplifier 125, resistors 139, 134 and
141 of operational amplifier 135 and resistors 149, 153, 154 and
151 of operational amplifier 145 may be proportioned to provide an
output signal which closely approximates the reciprocal of the
turbine expansion ratio-K factor curve of the engine.
The negative polarity weight of fuel flow signal is applied through
amplifier 18 to the dividend input terminal 21 of
divider-multiplier circuit 40 through lead 94 connecting output
terminal 19 of amplifier 18 to the dividend input terminal 21 of
divider-multiplier 40.
The positive polarity compressor discharge pressure signal is
applied through amplifier 16 to the divisor input terminal 22 of
divider-multiplier 40 through a lead 96 connecting output terminal
17 of amplifier 16 to the divisor input terminal 22 of
divider-multiplier 40.
The reciprocal of the turbine expansion ratio signal produced by
curve generator 26 is applied to the multiplier input terminal 23
of divider-multiplier 40 through a lead 97 connecting the output of
curve generator 26 to multiplier input terminal 23 of
divider-multiplier 40.
The positive polarity burner inlet temperature signal appearing
across variable resistor 13 is applied to the summing input
terminal 24 of divider-multiplier 40 through lead 89.
Simultaneously with the calculation of the turbine expansion ratio
by multiplier-divider 20, over those half cycles of the alternating
current reference signals during which output terminals 68 and 69
of the reference signal source of FIG. 3 are of a positive and a
negative polarity, respectively, with respect to point of reference
or ground potential 5, the positive polarity signal upon output
terminal 68, applied to the gate electrode of field effect
transistor 53, permits this device to conduct, and the negative
polarity signal upon output terminal 69, applied to the gate
electrodes of respective field effect transistors 54, 55 and 56,
holds these devices not conductive. While field effect transistor
53 conducts, the weight of fuel flow signal appears across load
resistor 90, curve B of FIG. 6. The negative polarity weight of
fuel flow signal, therefore, is applied to the inverting input
circuit terminal 43 of integrating operational amplifier 42 which
integrates this negative polarity dividend signal in a positive
direction for the duration of these half cycles of the reference
signals, as shown in curve D of FIG. 6. As the output signal upon
output circuit terminal 44 of integrating operational amplifier 42
is of a positive polarity, the output signal upon output circuit
terminal 52 of operational amplifier 50 is of a negative polarity.
With a negative polarity signal present upon the output circuit of
operational amplifier 50, type NPN-transistor 100 is not
conductive. Consequently, the potential upon junction 95 is of a
positive polarity. This signal is of no effect at this time as the
negative polarity reference signal maintains field effect
transistor 55 not conductive.
Over the alternate half cycles of the alternating current reference
signals during which output terminals 68 and 69 of the reference
signal source of FIG. 3 are of a negative and a positive polarity,
respectively, with respect to point of reference or ground
potential 5, the negative polarity output signal upon output
terminal 68 extinguishes field effect transistor 53 to remove the
weight of fuel flow signal from integrating operational amplifier
42 and the positive polarity signal upon output terminal 69 permits
field effect transistors 54 and 55 to conduct. Although this signal
is also applied to the gate electrode of reset field effect
transistor 56, this device is maintained not conductive by the
negative polarity signal present upon output circuit terminal 52 of
operational amplifier 50 which is applied to the gate electrodes
thereof. While field effect transistors 54 and 55 conduct, the
positive polarity compressor discharge pressure signal appears
across load resistor 91, curve C of FIG. 6, and simultaneously, the
positive polarity reciprocal of the turbine expansion ratio signal
appears across load resistor 92, curve F of FIG. 6. The positive
polarity compressor discharge pressure signal, therefore, is
applied to the inverting circuit terminal 43 of integrating
operational amplifier 42 which integrates this positive polarity
divisor signal in a negative polarity direction, as shown in curve
D of FIG. 6.
When integrating operational amplifier 42 has integrated the
compressor discharge pressure signal to substantially zero,
operational amplifier 50 switches to its alternate state in which
the output signal is of a positive polarity. This positive polarity
signal produces base-emitter current flow through type
NPN-transistor 100 to initiate collector-emitter current flow
therethrough. Upon the conduction of transistor 100 through the
collector-emitter electrodes, the potential upon junction 95 goes
negative and is applied to the gate electrode of field effect
transistor 55 which disconnects the reciprocal of the turbine
expansion ratio signal from the averaging circuit. Simultaneously,
the positive polarity signal upon output circuit terminal 52 of
operational amplifier 50 permits source-drain current flow through
reset field effect transistor 56, a condition which resets the
output signal upon output circuit terminal 44 of integrating
operational amplifier 42 to zero.
As the positive polarity burner inlet temperature signal is applied
to inverting input circuit terminal 46 of averaging operational
amplifier 45 this signal is summed with or added to the product of
the quotient of the weight of fuel flow signal divided by the
compressor discharge signal multiplied by the reciprocal of the
turbine expansion ratio signal. Consequently, the output signal
appearing across output terminals 98 and 99 of divider-multiplier
40 is a direct current potential signal of a negative polarity and
of a magnitude which is the analog representation of the turbine
inlet temperature which has been computed by the turbine inlet
temperature computer of this invention which calculated the
equation hereinabove set forth.
Although the foregoing description was on the basis of specific
electrical devices and electrical polarities, it is to be
specifically understood that alternate electrical devices and
compatible electrical polarities which produce the same results may
be substituted therefor without departing from the spirit of the
invention.
While a preferred embodiment of the present invention has been
shown and described, it will be obvious to those skilled in the art
that various modifications and substitutions may be made without
departing from the spirit of the invention which is to be limited
only within the scope of the appended claims.
* * * * *