U.S. patent number 3,902,316 [Application Number 05/514,426] was granted by the patent office on 1975-09-02 for deceleration detector.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Louis W. Huellmantel.
United States Patent |
3,902,316 |
Huellmantel |
September 2, 1975 |
Deceleration detector
Abstract
A regenerative gas turbine engine has a burner apparatus with a
combustion zone and a dilution zone therein and valve means for
controlling the amount of air flow into the combustion zone under
the control of a deceleration detector including a pressure sealed
housing with a movable diaphragm therein forming first and second
pressurizable chambers one of which senses discharge pressure of a
compressor driven by gas turbine means responsive to vehicle
deceleration produced by reduced fuel flow to the burner apparatus.
Orifice means in the diaphragm controls pressurization of the
chambers by the compressor and spring means are operative to
maintain contacts closed during steady state and increasing
compressor discharge pressure modes of operation so as to condition
the valve means for increased air flow to the combustion zone and
the orifice means serve to produce an imbalance of pressure across
the diaphragm under vehicle deceleration conditions so as to open
the contacts and thereby condition the valve means to reduce air
flow to the combustion zone.
Inventors: |
Huellmantel; Louis W. (Warren,
MI) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
24047073 |
Appl.
No.: |
05/514,426 |
Filed: |
October 15, 1974 |
Current U.S.
Class: |
60/39.23;
60/39.27; 60/794 |
Current CPC
Class: |
F23R
3/26 (20130101); F05B 2250/411 (20130101) |
Current International
Class: |
F23R
3/02 (20060101); F23R 3/26 (20060101); F02c
007/10 () |
Field of
Search: |
;60/39.23,39.27,39.29 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Gordon; Clarence R.
Attorney, Agent or Firm: Evans; J. C.
Claims
What is claimed is:
1. A deceleration control system for a gas turbine engine
comprising: burner apparatus having an outer case for receiving
combustion air, compressor means for supplying air to said outer
case, a burner liner located within said outer case including a
combustion zone and a dilution zone, throttle means for directing
fuel into said combustion zone, a first plurality of primary air
ports in said liner for directing air from the outer case into the
primary zone, a second plurality of ports in said liner for
directing air from the outer case into said dilution zone, valve
means operable to control the ratio of air directed into the
combustion zone and dilution zone, turbine means energized by the
burner apparatus connected to drive said compressor means and a
vehicle power shaft, a decelerator sensor including a pressure
sealed housing having a flexible diaphragm forming first and second
pressurizable chambers within said housing, a signal port in said
housing for directing discharge pressure from said compressor means
into one of said chambers, orifice means located between said first
and second chambers to maintain a balanced pressure thereacross
under steady state engine operation, switch means operated by said
diaphragm between open and closed position, spring means for
biasing said diaphragm to close said switch means during steady
state compressor discharge pressure operation, means responsive to
closure of said switch means to condition said valve means to
direct a predetermined amount of compressed air through the primary
air ports in said liner to the combustion zone during steady state
and increasing compressor discharge pressure operation, said first
pressurizable chamber having the pressure therein reduced during
engine deceleration and said orifice means being selected to retain
pressure in said second chamber to produce an unbalanced force
across said diaphragm in opposition to said spring means to produce
opening of said switch means, said valve means being responsive to
opening of said switch means to reduce flow of primary air into
said combustion zone to reduce the power supply to said turbine
means under vehicle deceleration conditions.
2. A turbine engine control system for regulating the output
temperature of a burner assembly in accordance with vehicle
operation comprising: compressor means having an inlet and an
outlet, turbine means including a power output shaft and means
connected to said compressor means to drive said compressor means
in accordance with vehicle acceleration and deceleration, a burner
apparatus including an outer case for receiving compressed air from
said compressor means, a burner liner within said outer case
including primary and secondary air ports therein, a combustion
zone within said liner in communication with said primary ports and
a dilution zone within said liner in communication with said
secondary air ports, throttle means for supplying fuel to said
combustion zone, valve means for varying the proportion of air flow
from the outer case through said primary and secondary air ports to
regulate the air flow into said combustion zone to control the
output temperature of said burner apparatus, a servo switch
including a pressure tight housing having a movable diaphragm
therein separating said housing into first and second pressurizable
chambers, a signal port in said housing for communicating said
first chamber with the compressor discharge pressure, orifice means
for communicating said first and second chambers to balance
pressure therein in accordance with compressor discharge pressure
under steady state and increasing compressor discharge pressure
operating conditions, switch means operated by said diaphragm
between open and closed positions, spring means for biasing said
diaphragm when pressure is balanced between said first and second
chambers to maintain said switch means closed, control means
responsive to closure of said switch means to condition said valve
means to direct an increased quantity of air into said combustion
zone, said orifice means being sized to maintain an imbalanced
pressure between said first and second chamber when the compressor
discharge pressure is reduced upon vehicle deceleration to cause
said diaphragm to move in opposition to said spring means to
condition said switch means open, said control means being
responsive to opening of said switch means to condition said valve
means to reduce the amount of air flow into said combustion zone
thereby to produce a reduced burner temperature outlet for reducing
output power from said turbine means under vehicle deceleration
conditions of operation.
3. A regenerative gas turbine comprising: in combination, air
compressor means, combustion apparatus supplied from said
compressor means said combustion apparatus including a combustion
products generator including a combustion zone and a dilution zone,
turbine means energized from the combustion apparatus connected to
drive said compressor means, a heat exchanger and a turbine exhaust
duct connected through one pass of the heat exchanger, said heat
exchanger having a second pass in heat exchange relation to the
first pass, a compressed air conduit leading from the compressor to
said second pass for directing air to the combustion apparatus,
said combustion apparatus including a liner having primary and
secondary air ports therein leading to said combustion zone and
dilution zone respectively, valve means for controlling the ratio
of air flow from the compressor into said combustion and dilution
zones for controlling the outlet temperature of said burner
apparatus, means for directing fuel to said combustion zone
including a throttle, said combustion apparatus being responsive to
a reduced flow of fuel upon vehicle deceleration to produce a
reduced temperature in said combustion apparatus with a resultant
decrease in output power from said turbine means, a deceleration
detector including a sealed housing having a signal port thereto
for sensing the discharge pressure of said compressor means, a
movable diaphragm within said sealed housing separating it into
first and second pressurizable chambers, orifice means for
communicating said first and second chambers to balance pressures
therebetween under steady state and increasing compressor discharge
pressure operation, switch means operated by said diaphragm between
open and closed positions, spring means for biasing said diaphragm
to hold said switch means closed when pressures are equalized in
said first and second chambers during steady state and increasing
modes of compressor discharge pressure operation, means responsive
to closure of said contacts to condition said valve means to
increase flow of air to said combustion zone, said orifice means
being operative during a decreasing compressor discharge pressure
produced by a deceleration mode of throttle operation to maintain a
greater pressure within one of said chambers to bias said diaphragm
against said spring means to open said switch means, said control
means being responsive to opening of said switch means to condition
said valve means to reduce the amount of air flow to the combustion
zone.
Description
This invention relates to regenerative gas turbine engines and more
particularly to improved means for controlling burner apparatus
therein in response to vehicle deceleration.
In control of regenerative gas turbine engines, variable geometry
burners are employed to reduce exhaust emissions. One approach has
been to include a movable valve element to control the flow of
primary air into a combustion zone of the burner. The gas
compressor for the regenerative engine decelerates under certain
conditions and in this case it has been found desirable to position
the valve element into a closed position to minimize air flow into
the burner combustion zone under vehicle deceleration conditions
and to position the valve open during vehicle acceleration to
produce more air flow as more fuel is directed to the burner.
Various fuel controllers have been proposed to regulate air/fuel
ratio to the burner of a gas turbine engine. Such controllers have
utilized various engine operating parameters such as sensing the
temperature of exhaust gases from the burner apparatus and/or
compressor discharge pressure so as to maintain a desired control
of the ratio of air/fuel flow to the burner apparatus.
An object of the present invention is to provide a simplified
control apparatus for maintaining a controlled air/fuel ratio to
the burner apparatus of a gas turbine engine by the provision of a
decelerator detector including means for detecting steady state and
increasing compressor discharge pressure as a basis of operation
and valve means responsive thereto to increase the flow of air from
a compressor into the burner apparatus combustion zone to maintain
a predetermined air/fuel ratio therein and further including means
responsive to a decrease in compressor discharge pressure
reflecting a decrease in fuel flow to the burner apparatus
combustion zone as occurs at vehicle deceleration to control the
valve means to reduce the amount of air flow into the combustion
zone so as to maintain the desired air/fuel ratio under vehicle
deceleration conditions.
Still another object of the present invention is to provide an
improved air/fuel ratio controller in a gas turbine engine
operative in response to compressor discharge pressure to vary the
amount of air flow into the combustion zone of burner apparatus so
as to maintain a desired air/fuel ratio thereto by the provision of
a detector having a gas tight body that houses a diaphragm to
define first and second pressure chambers one of which is in direct
communication with compressor discharge pressure and the other of
which is maintained under a balanced pressure by flow across
orifice means and wherein a pair of contacts are operated by the
diaphragm and maintained normally closed by spring means during
steady state, balanced pressure conditions to complete an
energization circuit to means for controlling a valve that will
maintain increased air flow to the combustion zone during vehicle
operations wherein the compressor is operated to produce a steady
state discharge pressure or an increasing discharge pressure and
wherein the orifice means responds to a decreasing compressor
discharge pressure to produce a pressure imbalance across the
diaphragm to condition the contacts open thereby to cause the valve
means to reduce the amount of air flow to the combustion zone under
vehicle deceleration operation thereby to maintain a desired
air/fuel ratio in the combustion zone.
Further objects and advantages of the present invention will be
apparent from the following description, reference being had to the
accompanying drawings wherein a preferred embodiment of the present
invention is clearly shown.
FIG. 1 is a diagrammatic view of a regenerative gas type turbine
engine including the present invention;
FIG. 2 is an enlarged, fragmentary cross sectional view taken along
the line 2--2 of FIG. 1, and
FIG. 3 is an enlarged cross sectional view of a deceleration
detector used in the present invention.
Referring now to the drawings, in FIG. 1 a regenerative type gas
turbine engine 10 as illustrated including a compressor 12 having
an inlet 14 and an outlet connected to a discharge conduit 16
connected to one end of a first heat exchange pass 18 in a
regenerator 20. The regenerator pass 18 is connected by an air
supply conduit 21 to an outer case 22 for a combustion or burner
apparatus 24. The burner apparatus 24 includes an inner liner 26
that has a combustion zone 28 therein in communication with a
plenum 30 defined by the outer case 22 around the liner 24 across a
plurality of primary air ports 31, 32 therein for supplying primary
combustion air to the combustion zone 28. A fuel supply for the
apparatus 24 is defined by a fuel line 34 connected across a fuel
control valve 36 to a fuel supply nozzle 38 for directing fuel into
the combustion zone 28 under the control of an accelerator throttle
40 coupled to valve 36. The throttle 40 controls the valve 36 to
direct fuel into the combustion zone 28 to provide an air/fuel
ratio in the combustion zone 28 for maintaining a temperature of
combustion to retard the formation of nitrogen oxides by
combination of nitrogen and oxygen present in the air supply to the
engine. Burner apparatus 24 further includes a plurality of
secondary or dilution air ports 42 therein that supply air into a
dilution zone within the liner 26 downstream of the combustion zone
28. A burner exhaust 44 directs combustion products across a
gasifier turbine 46 connected to a shaft 48 that is coupled to the
compressor 12 for driving it during burner operation. Exhaust from
the gasifier turbine 46 is directed through a power turbine 50
thence through an exhaust conduit 52 across a second heat exchanger
pass 53 of the regenerator 20 thence through an exhaust conduit 54
to atmosphere.
The power turbine 50 has an output shaft 56 that is coupled to a
power train for a vehicle.
Referring now to FIG. 2, the air flow to the combustion zone 28 is
under the control of an annular valve sleeve 58 that includes a
plurality of ports 60 at circumferentially spaced points
therearound that are located in overlying relationship to the
primary air flow ports 32 to control the proportion of air flow
through the primary air ports 32 and dilution ports 42 from the
plenum 30. The sleeve 58 as illustrated in FIG. 2 is in a closed
position wherein the primary air ports 32 are blocked by a
plurality of intermediate land portions 62 on the sleeve valve 58
between each of the ports 60 therein. A radially outwardly directed
lug 64 on the sleeve 58 is pivotally connected to one end of a link
66 that has its opposite end pivotally connected to an output shaft
68 of a fluid motor 70 including a cylinder 72 having a piston 74
slidably supported therein for opposite reciprocation between the
closed position shown in solid line in FIG. 2 and an open position
shown in dotted line in FIG. 2. The piston 74 is connected to shaft
68 and divides the cylinder 72 into chambers 76, 78 communicated
respectively by fluid lines 80, 82 that are connected to a
three-way solenoid valve 84. When the sleeve 58 is in a closed
position, the valve 84 is positioned to communicate a pressurized
source of air 86 through the pressure conduit 82 into the chamber
78 to force the piston 74 to the left as shown in solid line in
FIG. 2. Chamber 76 is then in communication with an exhaust port 88
of the valve 84. Conversely, when the fluid motor 70 is conditioned
to open the sleeve 58 the valve 84 will direct pressurized air from
the source 86 through the conduit 80 into the chamber 76 and the
chamber 78 will be exhausted through the port 88 to move the piston
74 to the right as shown in dotted line in FIG. 2. This will rotate
sleeve valve 58 to communicate ports 32, 60.
In the illustrated arrangement the solenoid valve 84 is under the
control of a deceleration detector 90 including a pressure sealed
housing made up of a first cover 92 of cup-shaped configuration
including a peripheral flange bent over at 94 into pressure sealed
relationship with a radially outwardly directed flange 96 on a
housing member 98. Housing member 98 includes a signal port 100
thereon that is communicated through a signal line 101 to sense
compressor discharge pressure in the conduit 16. The housing has a
movable flexible diaphragm 102 therein with its peripheral edge
press fit in sealing relationship between the flange 96 and the
flange 94. The diaphragm 102 separates the housing into first and
second pressure chambers 104, 106. A bleed orifice 108 is formed in
the diaphragm 102 to equalize the pressure between the chambers
104, 106.
The housing member 92 has an electrical contact 110 supported
thereon connected to a terminal 112 that is electrically connected
by a wire 114 to the solenoid 116 of the valve 84. The terminal 112
is electrically insulated from the body 92. A second contact 115 is
secured to the diaphragm 102 by suitable means representatively
shown as a rivet 116 so as to be moved with respect to the contact
110 between open and closed positions therewith. The contact 115 is
connected by means of a wire 118 to a second terminal 120 secured
to the body 92 and electrically insulated therefrom. Terminal 120
is electrically connected by means of a wire 122 to a suitable
source of power for the control circuit. The deceleration detector
90 further includes a coil spring 124 having one end thereof in
engagement with the diaphragm 102 and the other end thereof in
engagement with the housing portion 98 so as to bias the diaphragm
102 to maintain the contacts 110, 115 normally closed when pressure
is balanced between chambers 104, 106.
In operation the system responds to steady state vehicle operation
and vehicle operation that produces an increasing compressor
discharge pressure at the signal conduit 101 to produce a pressure
within the chambers 104, 106 that is equalized across the orifice
108. During these modes of operation the spring 124 will maintain
the contacts 110, 115 closed. This will condition the solenoid 116
to maintain the valve 84 to position piston 74 as shown in dotted
line in FIG. 2 so as to shift the sleeve 58 into a position to
cause the openings 60 therein to overlie the primary air ports 32
thus to maintain an increased level of air flow into the combustion
chamber 28 which corresponds to an increased fuel flow thereto
across the valve 36 in accordance with the position of throttle
40.
Under conditions where the vehicle is decelerated by movement of
the throttle 40 to reduce fuel flow to the combustion chamber 28,
reduced air flow to the combustion chamber 28 is required to
maintain a desired air fuel ratio to the combustor or burner
apparatus 24. Under vehicle deceleration the gas turbine shaft 48
will drive the compressor 12 at a reduced speed and will thereby
produce a mode of operation wherein the compressor discharge
pressure decreases. Assuming an initial steady state condition
wherein the pressure is balanced across the chambers 104, 106 the
chamber 106 pressure will be reduced relative to the pressure in
chamber 104 in response to the decreased compressor discharge
pressure. Moreover, the orifice 108 is sized to be sufficiently
small so that the pressure in the chamber 104 will be maintained
greater than that in the chamber 106 for a predetermined delay.
This will produce an unbalanced force on the diaphragm 102 acting
to the right as illustrated in FIG. 3, to overcome the spring force
to cause it to compress thereby resulting in the contacts 110, 114
being opened. At this point the energization of the solenoid 116
will condition the valve 84 to position the piston 74 in the solid
line position shown in FIG. 2 resulting in arcuate movement of the
sleeve 58 to the illustrated position in FIG. 2 to reduce the
amount of air flow into the combustion chamber 28 thereby to
maintain a desired air/fuel ratio therein to control the formation
of nitrogen oxides in the burner assembly 24.
The rate of compressor discharge pressure decrease which is
necessary to open the contacts 110, 115 and the duration of time
during which the contacts will remain open due to the imbalance of
pressure across the diaphragm 102 depends upon the volume of the
chambers 104, 106 along with the preload of the spring 124, its
rate and the size of the orifice 108. The reduction of air flow
into the combustion zone 28 during deceleration gives good burner
control during vehicle deceleration. The system is eadily
adjustable by use of a fine needle valve in place of the orifice
108 and an adjustable spring for positioning the fine needle valve.
Such an arrangement permits tailoring of the device for optimum
performance. Another advantage of the arrangement is that the
deceleration detector can also be utilized as a means to detect
gasifier decelerations under engine test conditions and thus has a
use for purposes other than burner control of the type illustrated
in FIG. 1.
While the embodiments of the present invention, as herein
disclosed, constitute a preferred form, it is to be understood that
other forms might be adopted.
* * * * *