U.S. patent number 3,581,492 [Application Number 04/839,994] was granted by the patent office on 1971-06-01 for gas turbine combustor.
Invention is credited to Francis M. Humenik, Carl T. Norgren, William H. Roudebush.
United States Patent |
3,581,492 |
Norgren , et al. |
June 1, 1971 |
GAS TURBINE COMBUSTOR
Abstract
Maintaining performance in a gas turbine combustor during
periods of airflow distortion. A diffuser duct is between a liner
forming the combustor and a housing surrounding the liner. Entry
ports in the combustor liner have scoops which extend the full
height of the diffuser duct to maintain the proper airflow
distribution regardless of inlet airflow distortion.
Inventors: |
Norgren; Carl T. (North
Olmsted, OH), Roudebush; William H. (North Olmsted, OH),
Humenik; Francis M. (Parma, OH) |
Assignee: |
|
Family
ID: |
25281186 |
Appl.
No.: |
04/839,994 |
Filed: |
July 8, 1969 |
Current U.S.
Class: |
60/804; 60/751;
431/352; 60/759 |
Current CPC
Class: |
F23R
3/06 (20130101) |
Current International
Class: |
F23R
3/04 (20060101); F23R 3/06 (20060101); F02c
003/06 () |
Field of
Search: |
;60/39.36,39.65
;431/352 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Dority, Jr.; Carroll B.
Claims
We claim:
1. A combustor for a gas turbine engine of the type having a
compressor and a turbine mounted on a spindle, said combustor
comprising
a curved liner forming a torus-shaped chamber encircling said
spindle between said compressor and said turbine, said liner having
a plurality of spaced ports therein, each of said ports having an
upstream edge toward said compressor and a downstream edge away
from said compressor;
means for injecting fuel into said torus-shaped chamber,
a housing surrounding said liner and spaced therefrom to form an
annular diffuser duct, said duct being in communication with said
compressor for receiving compressed air therefrom whereby
compressed air is admitted to said torus-shaped chamber through
said ports, and
a plurality of scoops in said diffuser duct adjacent some of said
ports and substantially surrounding said lines for intercepting a
portion of the flow of compressed air, each of said scoops having a
pair of spaced sidewalls extending from said liner toward said
housing, a backwall connecting the outermost edges of each of said
pairs of sidewalls whereby the space between the sidewalls at
adjacent ports is substantially unobstructed to the flow of
compressed air, said backwall extending the full height of said
diffuser duct from said downstream edge of said port to said
housing substantially opposite the upstream edge of said port, and
an open front between said sidewalls extending from said upstream
edge of said port to said housing whereby the mass airflow through
said open front and adjacent port into said combustion chamber is
proportional to the mass flow in said diffuser duct.
2. Apparatus as claimed in claim 1 wherein the ports are in at
least two adjacent rows, one of said rows being upstream from the
other,
primary entry ports being in said one row, and
secondary entry ports being in said other row.
3. Apparatus as claimed in claim 2 including scoops on the primary
entry ports.
4. Apparatus as claimed in claim 2 including scoops on the
secondary entry ports.
5. Apparatus as claimed in claim 2 wherein the primary entry ports
and secondary entry ports are aligned in the direction of
airflow.
6. Apparatus as claimed in claim 2 wherein the primary entry ports
and the secondary entry ports are staggered in the direction of the
airflow.
7. Apparatus as claimed in claim 1 wherein backwall portion of the
scoop comprises
a member curving outwardly from said downstream edge of the
adjacent port to the housing.
8. Apparatus as claimed in claim 1 wherein the backwall portion of
the scoop comprises
a substantially straight member extending diagonally outward from
said downstream edge of the adjacent port to a housing
substantially opposite the upstream edge of said port.
Description
ORIGIN OF THE INVENTION
The invention described herein was made by employees of the United
States Government and may be manufactured and used by or for the
Government for governmental purposes without the payment of any
royalties thereon or therefor.
BACKGROUND OF THE INVENTION
This invention is concerned with maintaining good performance in a
gas turbine combustor during periods of airflow distortion. The
invention is particularly directed to providing the proper airflow
through each entry port even if the radial flow profile from the
compressor is distorted.
Certain combustion problems have been encountered in gas turbine
engines due to flow distortions caused by acceleration,
deceleration, off design operation of the engine or local
environmental conditions. The problems have become critical in
advanced engines which operate near the maximum capability of the
materials from which the engine is constructed.
SUMMARY OF THE INVENTION
These problems have been solved in a gas turbine combustor
construction in accordance with the present invention wherein air
from the compressor is ducted into a single annular diffuser that
is adjacent the combustion chamber. The velocity profile across the
duct reflects the velocity profile at the compressor exit.
Air is admitted into the combustion chamber through entry ports in
a predetermined pattern. A scoop is attached to each entry port,
and each scoop extends completely to the full height of the
diffuser duct. In this manner the mass flow through the scoop and
into the combustion chamber is always proportional to the mass flow
from the compressor. Even if the radial flow profile from the
compressor becomes inverted, the airflow into each port will remain
the same. Thus the combustion chamber will contain the same fuel
air distribution which assures that no hot temperature streaks will
occur due to local decrease in airflow.
OBJECTS OF THE INVENTION
It is, therefore, an object of the present invention to maintain
good performance in a gas turbine combustor with no local
overheating during periods of flow distortion caused by
acceleration, deceleration, off-design operation, and local
environmental conditions.
Another object of the invention is to accommodate flow distortions
of air to a gas turbine combustor so that the engine can be
operated near the maximum capability of the materials.
These and other objects of the invention will be apparent from the
specification which follows and from the drawings wherein like
numerals are used throughout to identify like parts.
DESCRIPTION OF THE DRAWINGS
FIG. 1 is an axial quarter section view of a typical gas turbine
engine showing the relative positions of its various
components;
FIG. 2 is an enlarged sectional view of a prior art combustor;
FIG. 3 is an enlarged sectional view of a combustor constructed in
accordance with the present invention;
FIG. 4 is a perspective view of a combustor constructed in
accordance with the invention;
FIG. 5 is a perspective view of a portion of a combustor
illustrating an alternate embodiment of the invention; and
FIG. 6 is a plan view of still another embodiment of the present
invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring now to the drawings there is shown in FIG. 1 a gas
turbine engine 10 having a compressor 12 and a turbine 14 mounted
on a spindle 16. A combustor 18 enclosed by a housing 19 is
positioned between the compressor 12 and the turbine 14. Air from
the compressor 12 is heated in the combustor 18 and then directed
through the turbine 14 in a manner well known in the art.
One form of combustor has a torus-shaped chamber 20 between the
housing 19 and an inner casing 21 which encircles the spindle 16.
Fuel for combustion is injected into the chamber 20 through a
plurality of nozzles 22. Swirlers 24 may be used with the nozzles
22 for improved combustion.
The prior art combustor 18 is shown in greater detail in FIG. 2.
Air from the compressor 12 flows through an inlet passage 26 toward
a liner 27. This airflow is divided between an inner duct 28 and an
outer duct 30. The duct 28 is in the form of an annulus between the
inner casing 21 and the liner 27. The outer duct 30 comprises the
annular space between the housing 19 and the liner 27.
A portion of the air in the inlet passage 26 is also directed to
the swirlers 24 through snouts 31. The compressed air in the inner
duct 28 is admitted into the combustion chamber 20 through suitable
ports 32 and 34. In like manner, compressed air in the outer duct
30 passes through ports 36 and 38.
The arrows in the inlet passage 26 illustrate a distorted radial
air flow profile. The arrows in the ducts 28 and 30 show the
resulting distortions of the radial air profiles in these ducts. As
a result of these profile distortions the amount of air entering
the combustion chamber 20 through the ports 32, 34, 36, and 38 will
not be the same as with a uniform inlet airflow profile.
Consequently, combustion problems occur which may produce local
overheating.
A side entry combustor constructed in accordance with the present
invention in which air for the combustion process enters
substantially from a single annulus is shown in FIG. 3. Here again
compressed air from the compressor 12 flows through an inlet
passage 26 toward a liner 27. This air then passes into an annular
diffuser duct 40 that is adjacent to the combustion chamber 20
between the liner 27 and the housing 19. The radial air profile
across the diffuser duct 40 shown by the arrows in FIG. 3 will
reflect the radial air profile at the compressor exit in the
passage 26.
Air from the diffuser duct 40 is admitted into the combustion
chamber 20 in a predetermined entry pattern through primary entry
ports 42 and secondary entry ports 44 in the liner 27. Fuel is
supplied to the nozzles 22 from pipes 45. A portion of the air in
the inlet passage 26 is directed to the swirlers 24 at the nozzles
22 through inlet diffusers 46.
An important feature of the invention is the provisions of scoops
48 at the primary entry ports 42. The scoops 48 extend to the full
height of the diffuser duct 40 from the liner 27 to the housing 19.
Each scoop 48 has an open front which faces toward the flowing air.
A curved backwall 49 on each scoop 48 extends outward from the
downstream edge of each primary entry port 42 the full height of
the duct 40 to the housing 19. Vertical sidewalls 51 extend from
opposite edges of each primary port 42 to the curved backwall 49.
If desired, the wall 49 may be a straight plate which extends
diagonally from the downstream edge of the port 42 to the housing
19 opposite the upstream edge of the same primary port.
In this manner the mass flow through each scoop 48 and into the
combustion chamber 20 is always proportional to the mass flow from
the compressor. Even if the radial flow profile shown by the arrows
in FIG. 3 from the compressor becomes inverted the airflow into
each primary entry port 42 will remain the same. Thus the
combustion chamber 20 will have the same fuel air distribution
which, in turn, will assure that no hot temperature streaks will
occur due to local decreases in airflow.
The operation of the side entry combustor shown in FIG. 3 is
illustrated in greater detail in FIG. 4. The combustion chamber 20
encircles the spindle 16 which mounts the compressor at one end and
the turbine at the other. Fuel passes through pipes 45 and is
injected into the chamber 20 through nozzles as previously
described.
Compressed air from the compressor enters the diffuser duct 40 as
shown by the arrows A. A portion of this air is intercepted by the
scoops 48 at the primary entry port 42. These scoops 48 direct this
intercepted air into the combustion chamber 20. Still another
portion of the air enters the combustion chamber 20 through the
secondary ports 44.
A small amount of air passes through the inlet diffusers 46 into a
cooling duct 50 as shown by the arrow B. This cooling air passes
through cooling apertures 52 into the combustion chamber 20. The
remaining air from the diffusers passes to the swirlers 24 which
surround the nozzles 22.
DESCRIPTION OF ALTERNATE EMBODIMENTS
In the alternate embodiment shown in FIG. 5 scoops 54 are provided
at each of the secondary ports 44. The scoops 54 likewise extend to
the full height of the diffuser duct 40.
In the embodiment shown in FIGS. 4 and 5 the secondary ports 44 are
staggered relative to the primary entry ports 42. The embodiment
shown in FIG. 6 has the primary and secondary ports aligned. Each
primary port is provided with a scoop 56 that is aligned with
another scoop 58 on the secondary port. As seen in FIG. 6 the
secondary scoop 58 is larger than the primary scoop 56 to obtain
the proper proportioning of the air.
The embodiment shown in FIG. 6 also provides a set of secondary
ports 60 which are staggered relative to the primary entry ports.
This results in combinations of entry ports which may be sized to
suit desired combustor performance. When scoops are attached to
entry ports, the scoops extend to the full height of the diffuser
duct.
While several embodiments of the invention have been shown and
described it will be appreciated that various structural
modifications may be made without departing from the spirit of the
invention or the scope of the subjoined claims. For example, it is
contemplated the secondary ports 44 may be staggered with respect
to the primary ports 42 as shown in FIG. 5 yet have different size
scoops as shown in FIG. 6. Whatever the arrangement all the scoops
must extend to the full height of the diffuser duct to obtain at
all times correct proportional amount of air which is to be used
for combustion purposes. This amount of air is independent of the
compressor outlet radial velocity profile.
* * * * *