U.S. patent number 3,842,597 [Application Number 05/342,041] was granted by the patent office on 1974-10-22 for gas turbine engine with means for reducing the formation and emission of nitrogen oxides.
This patent grant is currently assigned to General Electric Company. Invention is credited to Frederic Franklin Ehrich.
United States Patent |
3,842,597 |
Ehrich |
October 22, 1974 |
GAS TURBINE ENGINE WITH MEANS FOR REDUCING THE FORMATION AND
EMISSION OF NITROGEN OXIDES
Abstract
Means for reducing the formation and emission of nitrogen oxides
in a gas turbine engine provide for bleeding and cooling a portion
of the airflow pressurized by the compressor. The cooled compressor
bleed airflow is then introduced into the primary combustion zone
of the combustor in order to reduce the flame temperature effecting
a reduction in the rate of formation of oxides of nitrogen.
Inventors: |
Ehrich; Frederic Franklin
(Marblehead, MA) |
Assignee: |
General Electric Company (Lynn,
MA)
|
Family
ID: |
23340084 |
Appl.
No.: |
05/342,041 |
Filed: |
March 16, 1973 |
Current U.S.
Class: |
60/226.1; 60/266;
60/728 |
Current CPC
Class: |
F23R
3/04 (20130101); F23R 3/10 (20130101); F02C
7/141 (20130101); F02C 7/185 (20130101); Y02T
50/60 (20130101); Y02T 50/675 (20130101); F28D
2021/0021 (20130101) |
Current International
Class: |
F23R
3/10 (20060101); F23R 3/04 (20060101); F02C
7/16 (20060101); F02C 7/18 (20060101); F02C
7/12 (20060101); F02C 7/141 (20060101); F02c
007/18 (); F02c 007/22 () |
Field of
Search: |
;60/39.65,39.66,39.67,39.23,39.07,DIG.10,226R,262,266,39.74R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Husar; C. J.
Assistant Examiner: Garrett; Robert E.
Claims
Having thus described one embodiment of the invention, what is
desired to be secured by Letters Patent is as follows:
1. In a gas turbine engine having a compressor, combustor and
turbine in serial flow relation, means for reducing the formation
of oxides of nitrogen within the combustor comprise:
means within said combustor defining a primary combustion zone, a
secondary combustion zone, and a dilution zone;
means for bleeding a portion of the airflow pressurized by the
compressor;
means for cooling the airflow bled from the compressor;
means for directing the unbled portion of compressor discharge
airflow to the primary combustion, secondary combustion, and
dilution zones of the combustor in order to support combustion in
the primary combustion zone;
and means for introducing the cooled compressor bleed airflow into
the primary combustion zone of the combustion in order to reduce
the flame temperature.
2. In a gas turbine engine of the bypass front fan type having a
core compressor, combustor and turbine in serial flow relation,
means for reducing the formation of oxides of nitrogen within the
combustor comprise:
means within said combustor defining a primary combustion zone, a
secondary combustion zone, and a dilution zone;
means for bleeding a portion of the airflow pressurized by the
compressor;
means for directing the airflow bled from the compressor into heat
exchange relation with the bypass airflow in order to cool the
compressor bleed airflow;
means for directing the unbled portion of compressor discharge
airflow to the primary combustion, secondary combustion, and
dilution zones of the combustor in order to support combustion in
the primary combustion zone, and
means for introducing the cooled compressor bleed airflow into the
primary combustion zone of the combustor in order to reduce the
flame temperature.
3. The gas turbine engine of claim 2 wherein the means for
directing the compressor bleed airflow into heat exchange relation
with the bypass airflow includes a heat exchanger having at least
two passages arranged in heat exchange relationship wherein one of
the passages receives and discharges bypass airflow and the other
passage receives and discharges compressor bleed airflow.
4. The gas turbine engine of claim 2 wherein the means for
reintroducing the cooled compressor bleed airflow back into the
primary zone of the combustor includes:
a spin chamber in general surrounding relation to a fuel injection
apparatus wherein the spin chamber receives the cooled compressor
bleed airflow and directs the airflow in a circular motion of ever
decreasing radius so as to generate a vortical flow around the fuel
injection apparatus, and,
conduit means communicating from the spin chamber to the heat
exchange means for directing the cooled compressor bleed airflow
therebetween.
5. The gas turbine engine of claim 4 wherein the spin chamber
includes:
an involute outer wall and generally planar spaced upstream and
downstream annular end walls, the outside edges of which are
peripherally joined to the outer wall and the inside edges of which
define an annular outlet which surrounds the fuel injection
apparatus;
a plurality of circumferentially spaced apart swirl vanes extending
between the upstream and downstream end walls in spaced apart
relation to the outer wall;
and an inlet in direct communication with the conduit means for
receipt of the cooled compressor bleed airflow.
Description
BACKGROUND OF THE INVENTION
This invention relates generally to a gas turbine engine having
means for significantly reducing the formation and emission of
nitrogen oxides and, more particularly, to a gas turbine engine
having means for cooling a portion of the compressor discharge air
and then introducing the precooled air into the primary combustion
zone to reduce the flame temperature and effect a corresponding
reduction in the formation of nitrogen oxides.
The present day emphasis on the elimination of air pollution has
resulted in a great deal of work and effort by aircraft gas turbine
engine manufacturers who have succeeded in significantly reducing
most forms of polluting emissions. Nitrogen oxides, however, are
one form of pollutant emitted from a gas turbine engine which have
not been satisfactorily reduced. Although it is not fully
understood how oxides of nitrogen are formed, it is believed that
such oxides are produced by the direct combination of atmospheric
nitrogen and oxygen at the high temperatures occurring in primary
combustion zones. The rates with which nitrogen oxides form depend
upon the flame temperature and consequently a small reduction in
flame temperature will result in a large reduction in the nitrogen
oxides.
One proposed solution for reducing the emission of nitrogen oxides
involves the introduction of more air to the critical primary
combustion zone during peak periods of nitrogen oxide formation.
The introduction of more air operates to reduce the fuel air ratio
and corresponding flame temperature. The formation of oxides of
nitrogen are generally most severe at the high power settings of
the engine such as during takeoff. However, if the engine were
designed to provide an excess of air during the peak power period
at takeoff, then the fuel to air ratio at low power settings or at
lightoff would likely be too lean to sustain or initiate
combustion. Therefore, it becomes necessary to provide variable
geometry apparatus to modulate the flow of air to the combustor in
a manner which provides an excess of air during high power settings
of the engine and reduces the airflow at low power setting to
prevent the combustor flame from blowing out. Variable geometry,
however, generally adds weight and complexity to a gas turbine
engine and consequently is not an entirely satisfactory solution to
the problem of eliminating nitrogen oxide emissions.
Another proposed solution for reducing the emission of nitrogen
oxides relates to the effect of vitiating the combustion air with
inert products such as recirculated cooled exhaust products or
steam, wherein the flame temperature is reduced mainly by dilution
and by the increased specific heat of the mixture. One difficulty
with recirculating cooled exhaust products or steam, however, is
that the combustor is generally at a higher pressure than the
exhaust necessitating the addition of a pump or blower to introduce
the exhaust products directly into the combustor. The addition of a
pump or blower again adds weight and complexity to the gas turbine
engine with an attendant reduction in engine efficiency.
The addition of a pump or blower could be eliminated by
reintroducing the exhaust products directly into the compressor
inlet; however, this method also incurs certain disadvantages.
Foremost is the increased risk that air contaminated by exhaust
products will be circulated through the aircraft cabin from
malfunctioning airconditioners which utilize compressor bleed air.
Also, introducing exhaust products into the compressor inlet would
accelerate the overall corrosion within the compressor.
Still another proposed solution for reducing the emission of
nitrogen oxides relates to the introduction of a spray of water
into the primary combustion zone in order to lower the flame
temperature. This, however, necessitates that water storage tanks
and pumps be added to the aircraft which could significantly
increase the weight of the aircraft.
Therefore, it is a primary object of this invention to provide a
simple means for reducing the formation and emission of nitrogen
oxides from the combustor of a gas turbine engine without the use
of variable geometry, blowers, pumps or water storage tanks.
It is also an object of this invention to provide a simple means
for lowering the flame temperature within the primary combustion
zone of a gas turbine engine in order to reduce the formation of
nitrogen oxides therein.
It is a further object of this invention to provide a simple means
for cooling a portion of the compressor discharge air and then
introducing the precooled air into the primary combustion zone to
quench the thermal reaction and reduce the formation of nitrogen
oxides.
SUMMARY OF THE INVENTION
Briefly stated, the above and other objects are achieved in the
present invention by providing a gas turbine engine which may be of
the bypass front fan type having a core compressor, combustor and
turbine in serial flow relation, with a simplified means for
reducing the formation of oxides of nitrogen within the combustor.
In the gas turbine engine, there is included means for bleeding a
portion of the airflow pressurized by the compressor together with
means for directing the airflow bled from the compressor into heat
exchange relation with the bypass airflow in order to cool the
compressor bleed airflow. Means are further included for
introducing the cooled compressor bleed airflow into the primary
combustion zone of the combustor in order to reduce the flame
temperature and rate of formation of oxides of nitrogen.
BRIEF DESCRIPTION OF THE DRAWINGS
While the specification concludes with claims distinctly claiming
and particularly pointing out the invention described herein, it is
believed that the invention will be more readily understood by
reference to the discussion below and the accompanying drawings in
which:
FIG. 1 is a side view, partly in cross-section, of a gas turbine
engine embodying means for reducing the formation of nitrogen
oxides within the engine combustor.
FIG. 2 is a partial cross-sectional view of the forward end of a
gas turbine engine combustor embodying means for reducing the
formation of nitrogen oxides therein.
FIG. 3 is a perspective view, partly cut away, of the nitrogen
oxide reducing means of FIG. 2.
FIG. 4 is a side view, partly in cross-section, of a gas turbine
engine embodying an alternate embodiment of the means of FIG. 1 for
reducing the formation of nitrogen oxides within the engine
combustor.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring now to FIG. 1, there is shown a gas turbine engine 10 of
the bypass front fan type comprising a core engine 12 having a
compressor 14, a combustor 16, a gas generator turbine 18 for
driving the compressor 14, and a power turbine 20 arranged in
axially spaced serial flow relationship. The inner turbomachine, or
core engine 12, is enclosed within a cylindrical casing 22 which
terminates at its downstream end in an exhaust nozzle 24 through
which the combustion products of the core engine 12 may be
discharged to produce thrust. To provide additional thrust a fan 26
is mounted upstream of the core engine 12 and is driven by the
power turbine 20. The fan 26 is comprised of a plurality of fan
blades 28 which extend radially outward from a fan wheel 30, which
is coupled for rotation with the power turbine 20 through the
interconnecting shaft 31. The fan blades 28 extend radially across
a bypass duct or passageway 32 defined between an outer cylindrical
casing 34 and a "bullet nose" 36 located upstream of the fan blades
28. Downstream of the fan blades 28, the passageway 32 is divided
into two passages 38 and 40 by the casing 22. Radially positioned
between the casing 34 and casing 22 are a plurality of fan stator
vanes 42 which are followed by a plurality of fan outlet guide
vanes 44. Thus a portion of the air entering the passageway 32
flows through the fan blades 28 into the passageway 38, through the
stator vanes 42, and through the outlet guide vanes 44 and
thereafter exits through an outlet opening 46 formed by the casing
34 and the casing 22. Since this air is pressurized in flowing
through the fan blades 28, it provides forward thrust to the
turbofan engine 10.
The remainder of the air flowing through the passageway 32 and fan
blades 28 enters the passageway 40. Located within this passageway
40 are a plurality of inlet guide vanes 48 for the core engine 12
which may be followed by a plurality of rotatable booster blades
50, extending from a disc 52 and coupled for rotation with the fan
blades 28 by means of the disc 52 and a shaft 54. Located
downstream of the booster blades 50 is a row of stator vanes 56.
Air passing through the stator vanes 56 next flows into the core
engine 12 through passageway 58.
The gas turbine engine 10 may be either a high bypass ratio machine
or a low bypass ratio machine wherein the "bypass ratio" refers to
the ratio of the mass flow of fluid in the bypass passageway 38 to
the mass flow in the core engine 12 (or passageway 40).
The compressor 14 discharges pressurized air through a plurality of
circumferentially spaced apart outlet guide vanes 60 which extend
radially between the walls of a diffuser passageway 62. A portion
of the pressurized air exiting from the diffuser passageway 62 is
bled through a conduit 64 to a heat exchanger 66. The heat
exchanger 66 receives a portion of the cool bypass airflow from
passageway 38 through inlet 68 whereupon the bypass airflow is
directed through conduit 70 in heat exchange relation with the
compressor discharge air and then discharged back into the bypass
passageway 38 through outlet 72. Whereas the temperature and
pressure of the compressor discharge air has been raised by the
compressor 14, the heat exchanger 66 operates to reduce the
temperature of that portion of the compressor discharge air bled
through conduit 64.
The heat exchanger herein described is of conventional design and
may take on many different forms with the only requirement being
that the bypass airflow be used to cool a portion of the compressor
discharge air. In practice the heat exchanger 66 may be annular
with the fluids passed through the heat exchanger in paths as
illustrated. If desired, however, alternative flow arrangements can
be used for providing more effective heat transfer. For example,
each of the streams could be directed through the heat exchanger
twice in radial outflow passes. It is thus essential that there be
two sets of independent passages disposed in heat exchange
relationship within the heat exchanger, the bypass air flowing
through one set of passages and the compressor discharge air
flowing through the other set of passages.
The cooled compressor discharge air exiting from the heat exchanger
66 is directed to the combustor 16 by way of conduit 74 from whence
it is dumped into the primary combustion zone 76 of the combustor
16. Fuel from a source of pressurized fuel (not shown) is
introduced into the primary zone 76 of combustor 16 through fuel
nozzle 78. Once the fuel is introduced into combustor 16, it may be
ignited by igniter 80. The primary combustion zone 76 is generally
defined within liner 81 in the area adjacent fuel nozzle 78.
In operation, combustor 16 will generally emit the following
combustion products: carbon monoxide, carbon dioxide, water vapor,
smoke and particles, unburned hydrocarbons, nitrogen oxides and
sulfur oxides. Of these, carbon dioxide and water vapor may be
considered normal and unobjectionable. Smoke can be a problem;
however, it is generally controlled by design modifications in the
primary combustion zone. Particulates which are one form of smoke
are generally associated with coal burning plants and are not of
immediate concern to gas turbines. Sulfur oxides can be limited by
the careful selection of fuels low in total sulfur. This leaves
carbon monoxide, unburned hydrocarbons and nitrogen oxides as the
emissions of primary concern in the gas turbine engine.
As previously discussed, it is not fully understood how oxides of
nitrogen are formed; however, it is believed that such oxides are
produced by the direct combination of atmospheric nitrogen and
oxygen at the high temperatures occurring in primary combustion
zones. The presence of organic nitrogen in the fuel may also aid in
the production of nitrogen oxides together with the atmospheric
nitrogen. The rates with which nitrogen oxides form depend upon the
flame temperature and, consequently, a small reduction in flame
temperature will result in a large reduction in the nitrogen
oxides.
Previously suggested means for reducing the maximum temperature in
the primary zone of a gas turbine combustor have included schemes
for introducing more air at the primary combustion zone,
recirculating cooled exhaust products or steam back into the
primary combustion zone and injecting a water spray back into the
primary zone. All of these previously suggested methods, however,
involve the addition of either complex or heavy hardware such as
variable geometry, blowers, pumps or water storage tanks.
The invention herein described, however, provides for a heat
exchanger 66 which precools a portion of the compressor discharge
air and directs the precooled compressor discharge air back to the
primary combustion zone 76 through conduit 74 in order to reduce
the flame temperature thereby inhibiting the formation of oxides of
nitrogen. Although it is preferred that a portion of the compressor
discharge air be precooled, it would not be outside the scope of
invention to bleed and cool a portion of the compressor interstage
air and redirect the precooled compressor interstage air back to
the primary zone of the combustor.
Referring now to FIGS. 2 and 3 where like numerals refer to
previously described elements, there is shown one arrangement by
which the precooled compressor discharge air may be introduced into
the primary combustion zone 76. An outer shell 82 is provided to
enclose the liner 81 and to cooperate therewith to form passageways
84, 86 surrounding the liner 81. As will be understood, the
passageways 84, 86 are adapted to deliver a flow of pressurized air
from the compressor 14 through suitable apertures or louvers 88. In
this manner, the passageways 84, 86 act to both cool the liner 81
and to provide dilution air to the gaseous products of combustion
formed within the primary combustion zone 76.
The upstream end of liner 81 is adapted to function as a flow
splitter to divide the pressurized air delivered from the
compressor 14 between the passages 84, 86 and an upstream end
opening 90. Located within the liner 81 is a conventional fuel
injecting apparatus shown generally at 92 which may be of the
atomizing type as is well known in the art. Pressurized fuel may be
supplied to the fuel injection apparatus 92 through a conduit 94
which extends through the outer shell 82 and communicates with a
source of pressurized fuel (not shown).
Surrounding the fuel injection apparatus 92, there is a housing 96
which comprises an involute outer wall 97 and generally planar,
spaced upstream and downstream annular end walls 98 and 100,
respectively, which are peripherally joined to the outer wall 97. A
plurality of circumferentially spaced apart swirl vanes 101 extend
between the upstream and downstream end walls in spaced apart
relation to the outer wall 97. The housing 96 defines a
conventional spin chamber 102 having an annular outlet 104 which
surrounds the fuel injection apparatus 92. The outer wall 97 is of
spiral shape with progressively decreasing radius from an inlet 106
to a terminal edge or lip 108 which in part defines the opening
from inlet 106 to the spin chamber 102. The inlet 106 is in direct
flow communication with the conduit 74 for receiving a flow of
precooled compressor discharge air directly from the heat exchanger
66. In this manner precooled compressor discharge air may be
directed from inlet 106 into the spin chamber 102 in a circular
motion of ever decreasing radius so as to generate a vortical flow
around the fuel injection apparatus 92.
In operation, a portion of the compressor discharge air is bled
through inlet 110 of conduit 64 and directed to the heat exchanger
66 whereupon it is circulated in heat exchange relationship with
the fan bypass airflow, and then directed to the spin chamber 102
via conduit 74. The precooled compressor discharge air is dumped
into the primary combustion zone 76 in a vortical flow from outlet
104 of the spin chamber 102 whereupon it reduces the flame
temperature in the primary combustion zone 76 and inhibits the
formation of oxides of nitrogen.
Turning now to FIG. 4 where like numerals refer to previously
described elements, there is shown a modified gas turbine engine
10' which is also of the bypass front fan type, and which includes
an extended cowling or casing 34' The cowling 34' is spaced apart
from the core engine 12 so as to define a bypass passageway 38'
which extends substantially the length of the core engine 22 and
terminates in an outlet opening 46'. A heat exchanger 66' is
disposed within the passageway 38' and receives a portion of the
pressurized compressor discharge air exiting from the diffuser
passageway 62 through conduit 64'. The compressor discharge air is
directed into heat exchange relation with the comparatively cooler
fan air flow in passageway 38', and then returned to the combustor
16 through conduit 74' in order to reduce the flame temperature and
inhibit the formation of oxides of nitrogen as previously
discussed.
From the foregoing it will be appreciated that the formation of
nitrogen oxide in the combustor of a gas turbine engine are
inhibited by simple means without the addition of variable
geometry, blowers, pumps or water storage tanks. It will also be
appreciated that a portion of the compressor discharge air which is
bled and cooled by the heat exchanger 66 may be directed to the
turbine for cooling purposes. Accordingly, while preferred
embodiments of the present invention have been depicted and
described, it will be appreciated by those skilled in the art that
many modifications, substitutions, and changes may be made thereto
without departing from the invention's fundamental scheme.
* * * * *