U.S. patent number 3,869,864 [Application Number 05/368,576] was granted by the patent office on 1975-03-11 for combustion chambers for gas turbine engines.
This patent grant is currently assigned to Lucas Aerospace Limited. Invention is credited to George Edward Bunn.
United States Patent |
3,869,864 |
Bunn |
March 11, 1975 |
COMBUSTION CHAMBERS FOR GAS TURBINE ENGINES
Abstract
A combustion chamber for a gas turbine engine comprises a flame
tube surrounded by an air passage, fuel sprayer(s) at one end of
the flame tube and a combustion gas outlet at the end. A number of
sets of apertures are formed by corrugated portions of the wall to
cause air entering the flame tube to flow along the wall thereof.
Baffles project from the wall and are disposed in the flow path of
the air flowing along the wall. Projections extend from the baffles
substantially parallel to the wall and towards the apertures formed
by the respective corrugated portions.
Inventors: |
Bunn; George Edward (Clitheroe,
EN) |
Assignee: |
Lucas Aerospace Limited
(Birmingham, EN)
|
Family
ID: |
10255088 |
Appl.
No.: |
05/368,576 |
Filed: |
June 11, 1973 |
Foreign Application Priority Data
|
|
|
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Sep 6, 1972 [GB] |
|
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27154/72 |
|
Current U.S.
Class: |
60/757; 60/758;
60/804; 60/749; 60/760 |
Current CPC
Class: |
F23R
3/16 (20130101); F23R 3/12 (20130101) |
Current International
Class: |
F23R
3/02 (20060101); F23R 3/16 (20060101); F23R
3/04 (20060101); F23R 3/12 (20060101); F02c
007/18 () |
Field of
Search: |
;60/39.65,39.66,39.36 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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|
|
|
|
|
|
943,250 |
|
Dec 1963 |
|
GB |
|
1,150,344 |
|
Apr 1969 |
|
GB |
|
721,899 |
|
Jan 1955 |
|
GB |
|
Primary Examiner: Husar; C. J.
Assistant Examiner: Garrett; Robert E.
Attorney, Agent or Firm: Holman & Stern
Claims
I claim:
1. A combustion chamber for a gas turbine engine, comprising a
flame tube, an air supply passage separated from said flame tube by
a wall thereof, means defining a plurality of apertures in said
wall providing communication between said air supply passage and
the interior of said flame tube, each of said apertures being
adapted to cause a flow of air along said wall within said flame
tube, baffles projecting from said wall within said flame tube for
deflecting air passed, in use, along said wall from at least some
of said apertures, and projections spaced from said wall and
extending from said baffles in a direction transverse to the
direction of extent of said baffles whereby circulation of gas, in
use, is established and maintained in the desired flow pattern.
2. The combustion chamber according to claim 1, wherein said
baffles comprise strips each of which is attached at one side
thereof to said wall within said flame tube and is provided with a
series of spaced recesses at the other side thereof, and said
projections extend from said baffles at the bases of said recesses
in a direction upstream of the respective baffles relative to the
air whose circulation is promoted thereby.
3. The combustion chamber according to claim 1, wherein some of
said apertures are adapted to cause a flow of air along said wall
within said flame tube by being provided with baffles which extend
substantially parallel to said wall in the vicinity of said
apertures and some of said apertures are formed in portions of said
wall which extend transversely to wall portions on either side
thereof so that air is introduced along the last-mentioned
portions.
4. The combustion chamber according to claim 3, wherein said
baffles carrying said projections are disposed adjacent said
apertures formed in the transversely extending wall portions, said
projections extending towards the last-mentioned apertures.
Description
This invention relates to combustion chambers for gas turbine
engines.
According to the present invention, there is provided a combustion
chamber for a gas turbine engine, comprising a flame tube, an air
supply passage separated from the flame tube by a wall thereof [or
of the flame tube] a plurality of apertures in the wall providing
communication between the air supply passage and the interior of
the flame tube some of the apertures being adapted to cause a flow
of air along the wall within the flame tube baffles projecting from
the wall within the flame tube for deflecting air passed, in use,
along the wall from at least some of the said apertures, and
projections spaced from the wall and extending from the baffles in
a direction transverse to the direction of extent of the baffles
whereby circulation of gas, in use, is established and maintained
in the desired flow pattern.
Preferably, the said baffles comprise strips which are attached to
the wall within the flame tube at one side thereof and are provided
with a series of spaced recesses at the other side thereof and the
projections extend from the baffles at the bases of the recesses in
a direction upstream of the respective baffles relative to the air
whose circulation is promoted thereby.
Most advantageously, some other of the apertures are adapted to
cause a flow of air along the wall within the flame tube by being
provided with baffles which extend substantially parallel to the
wall in the vicinity of the apertures and some of the apertures are
formed in portions of the wall which extend transversely to
portions on either side of the wall so that air is introduced
transversely with respect to said portions. Advantageously, the
baffles carrying the projections are disposed adjacent the last
mentioned apertures with the projections extending towards said
apertures.
An embodiment of the present invention will now be described, by
way of example, with reference to the accompanying drawings in
which:
FIG. 1 is a sectional view through part of a combustion chamber
according to the present invention, and
FIG. 2 is a section on the line A--A of FIG. 1.
Referring to the drawing, the combustion chamber comprises an
annular flame tube 1 surrounded by an annular air supply passage 2
which is separated from the flame tube 1 by a generally toroidal
wall 3 of the flame tube 1.
An annular air inlet 4 serves to supply air to the air supply
passage 2 and a series of fuel injectors 5 serve to inject fuel
into the flame tube 1 together with primary air from the air supply
passage 2. The flame tube 1 is provided with an annular exhaust
outlet 6.
The wall 3 is of fabricated construction and has formed therein
series of apertures 7, 8 and 9 which provide communication between
the air supply passage 2 and the interior of the flame tube. The
series of apertures 7 are baffled by baffles 10 so that air is
introduced along the inside of the wall 3 to enhance cooling of the
wall 3. The series of apertures 8 are similarly baffled by means of
baffles 11 to provide flow along the wall 3, but the baffles 11
direct flow of air in a direction away from the exhaust outlet 6
and towards the fuel injectors 5. The series of apertures 9 are
formed by a pair of annular corrugated strips 12 (see FIG. 2)
disposed between adjacent, overlapping portions of the wall 3, the
corrugated strips 12 forming, in effect, a portion of the wall 3
which extends transversely to portions of the wall on either side
thereof. In this manner, the series of apertures 9 are disposed to
admit air into the flame tube 1 along the wall 3. It will be seen
from FIG. 1 that the series of apertures 9 formed in the outer
portion of wall 3 serve to direct air towards the fuel injectors 5
whilst the series of apertures 9 in the inner portion of the wall 3
serve to direct air from the fuel injectors 5. At a location which
is downstream of the series of apertures 9, there are provided
respective baffles 13 which project from the wall 3 internally of
the flame tube 1 and are formed by annular strips attached at one
of their sides to the wall 3 whilst the other sides thereof which
extend into the flame tube 1 are provided with a series of spaced
recesses 14. Furthermore, a plurality of spaced projections 15 are
provided on each baffle 13 to project perpendicularly therefrom at
the bases of the spaced recesses 14. It will be seen from FIG. 1
that each projection 15 extends substantially parallel to the wall
3 to which its associated baffle 13 is attached and towards the
series of apertures 9 associated with the baffle 13.
The baffle 13 attached to the inner portion of the wall 3 is also
disposed adjacent one of the series of apertures 8 so that air
entering the flame tube 1 from that series of apertures 8 is
deflected not only by baffle 11 associated therewith but also by
the surface of the baffle 13 remote from the projections 15. On the
opposite sides of the baffle 13 to the series of apertures 9 on the
outer portion of the wall 3 are provided a further series of
apertures 16 providing direct communication between the air passage
2 and the flame tube 1, these series of apertures 16 being
unbaffled and extending with their axes in a radial direction with
respect to the axis of the flame tube 1.
It is considered that the above described combustion chamber is
particularly efficient since almost all the air, some 96% is used
for cooling purposes and is then deflected by the baffles 13 with
projections 15, to participate in the combustion process. In
contrast, in conventional arrangements about 40% of the air is
introduced as cooling air which is largely confined to regions
close to the flame tube wall and is not deflected to participate in
the combustion process. This latter arrangement has an undesirable
effect on the temperature distribution at the outlet of the
combustion chamber.
* * * * *