U.S. patent number 3,724,207 [Application Number 05/169,307] was granted by the patent office on 1973-04-03 for combustion apparatus.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Douglas Johnson.
United States Patent |
3,724,207 |
Johnson |
April 3, 1973 |
COMBUSTION APPARATUS
Abstract
A combustion apparatus having outer and inner casing walls and
an annular combustion liner mounted between them. The combustion
liner is supported at its upstream end by brackets extending from
the front wall of the liner having a radial slip fit connection
with struts connecting the outer and inner casings. An annular
diffuser fitting against the front end of the combustion liner and
extending from and between the struts supplies air to the front
wall of the combustion liner. Fuel is introduced through combined
fuel and air inlet structures spaced around the front wall of the
liner, these having an outer air entrance, an intermediate mixed
fuel and air entrance, and an inner air entrance all flaring at the
inner side of the combustion liner front wall to direct the
entering air and fuel generally radially from these entrances.
Inventors: |
Johnson; Douglas (Indianapolis,
IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
22615110 |
Appl.
No.: |
05/169,307 |
Filed: |
August 5, 1971 |
Current U.S.
Class: |
60/743; 60/756;
60/751; 239/424 |
Current CPC
Class: |
F23R
3/10 (20130101); F23R 3/60 (20130101); Y02T
50/675 (20130101); Y02T 50/60 (20130101) |
Current International
Class: |
F23R
3/04 (20060101); F23R 3/00 (20060101); F23R
3/10 (20060101); F23R 3/60 (20060101); F02c
003/24 () |
Field of
Search: |
;60/39.74R ;239/424 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Hart; Douglas
Claims
I claim:
1. Combustion apparatus comprising, in combination, means defining
a combustion space and having an upstream wall, the said wall
defining at least one opening for admittance of fuel and air; a
double-walled boss mounted on the said wall projecting through the
opening with the inner wall of the boss flaring downstream of the
opening to define a flange, the boss having air entrances at its
upstream end to admit air for flow between the walls of the boss
and discharge over the upstream side of the flange; a tubular air
duct mounted within and spaced from the boss, the air duct having a
flaring head overlying and spaced downstream from the said flange;
a baffle mounted on the air duct overlying and spaced downstream
from the head to direct the air emerging from the duct generally
radially of the duct; the said boss and duct defining between them
an annular conduit for fuel and air terminating in a flaring
discharge port between the said flange and the said head; and means
for introducing fuel into the air flowing through the said conduit;
flow of air through the boss, the said annular conduit, and the
said air duct resulting from a pressure drop across the wall in
operation of the combustion apparatus.
2. Combustion apparatus comprising, in combination, means defining
a combustion space and having an upstream wall, the said wall
defining at least one opening for admittance of fuel and air; a
double-walled boss mounted on the said wall projecting upstream
from the opening with both walls of the boss flaring downstream of
the opening to define flanges; means mounting the outer flange on
the upstream wall; the boss having air entrances at its upstream
end to admit air for flow between the walls of the boss and
discharge over the upstream side of the inner wall flange; a
tubular air duct mounted within and spaced from the boss, the air
duct having a flaring head overlying and spaced downstream from the
said flange; a baffle mounted on the air duct overlying and spaced
downstream from the head to direct the air emerging from the duct
generally radially of the duct; the said boss and duct defining
between them an annular conduit for fuel and air terminating in a
flaring discharge port between the said flange and the said head;
means for introducing fuel into the air flowing through the said
conduit; means for inducing turbulence in the air flowing through
the said conduit to promote atomization and mixture of the fuel
with the air; flow of air through the boss, the said annular
conduit and the said air duct resulting from a pressure drop across
the wall in operation of the combustion apparatus.
Description
The invention herein described was made in connection with work
under a contract with the Department of Defense.
My invention relates to combustion apparatus and, particularly,
combustion apparatus of the type employed in aircraft gas turbine
engines. In these, there are particular requirements of light
weight, compactness, efficient combustion, and minimization of
smoky combustion and other combustion phenomena which may produce
undesirable combustion products.
My invention is concerned with improved arrangements for the
admission of fuel in intimate association with air for clean
combustion and also with improved structural arrangements of the
elements of a combustion chamber.
Combustion chambers for gas turbines generally fall into three
types: The can type in which a combustion liner is disposed within
an outer case, generally in more or less concentric relation to it,
the can-annular type in which a number of more or less cylindrical
combustion liners are disposed in generally parallel relation
within an annular air space, and the full annular type in which an
annular combustion liner is disposed within an annular air space.
The last-named tends to be the lightest and most compact. However,
the attainment of optimum supply and circulation of fuel and air in
an annular combustion space is generally more difficult than in one
of circular cross section.
My invention is directed to provision of combustion apparatus
better suited to the requirements of practice than those now known
and, more particularly, to provide improved structural relations of
the parts of a combustion apparatus and superior arrangements for
admission of fuel and air in intimate mixture for complete
combustion within a compact flame zone.
The nature of my invention and its advantages will be clear to
those skilled in the art from the succeeding detailed description
of the preferred embodiment of the invention and the accompanying
drawings thereof.
FIG. 1 is a sectional view of the forward portion of an annular gas
turbine combustion apparatus taken on a plane containing the axis
of the apparatus.
FIG. 2 is a fragmentary view of the front end of the combustion
liner, with parts in section, taken on the plane indicated by the
line 2--2 in FIG. 1.
FIG. 3 is a fragmentary view looking forward toward the front wall
of the combustion liner, taken on the plane indicated by the line
3--3 in FIG. 1.
FIG. 4 is a plan view of a portion of the exterior of the
combustion apparatus with parts cut away, as indicated by the line
4--4 in FIG. 1.
FIG. 5 is a partial sectional view taken on a plane containing the
axis of the combustion apparatus and angularly displaced from the
section of FIG. 1.
FIG. 6 is a fragmentary view illustrating a modification, taken on
the plane illustrated by the line 6--6 in FIG. 3.
Referring first to FIG. 1, the combustion apparatus comprises a
case 2 including an outer casing 3 and an inner casing 4 defining
between them a space 6 for compressed air delivered from a source
such as the compressor of a gas turbine engine through a diverging
annular inlet 7. Combustion takes place within a space 8 inside a
combustion liner 10 defined by an outer wall 11, an inner wall 12,
and an annular front wall 14. The walls 11 and 12 are typically of
a segmented structure with successive segments defining inlets 15
for film cooling air to flow along the hot side of the liner to
protect it from the flame. This film, cooling air may form part of
the air for combustion and may also form part of the air for
dilution of the combustion products. The specific wall structure is
immaterial to the invention. Various arrangements of segmented
liners for film cooling of the liner are shown for example in U.S.
patents to Seippel U.S. Pat. No. 2,268,464, Dec. 30, 1941; Way U.S.
Pat. No. 2,448,561, Sept. 7, 1948; Christensen U.S. Pat. No.
2,537,033, Jan. 9, 1951; and DeZubay et al. U.S. Pat. No.
2,573,694, Nov. 6, 1951. All but the first named of these show full
annular combustion apparatus.
The outer and inner liner walls together with the front wall form
an annular basket-like rigid structure, the front end of which is
supported from the combustion apparatus outer case. The downstream
or outlet end of the combustion liner (not shown) is suitably
supported from the casing 2, ordinarily by being coupled to a
turbine nozzle fixedly mounted with respect to the combustion
apparatus. All or a major part of the air for complete combustion
of the fuel is admitted to the combustion liner through the front
wall 14. This air is supplied through a flow divider or splitter 16
having diverging outer and inner walls 18 and 19. This structure is
cast integral with or welded to a plural number, such as six, of
struts 20 (FIG. 5) which extend from the outer casing 3 to the
inner casing 4 upstream of wall 14. The splitter is thus positively
supported in the combustion apparatus case 2. Combustion air inlets
22 are defined in the leading edge of the splitter 16. These
deliver a portion of the air supplied by the engine compressor into
a space 23 bounded by walls 14, 18, and 19. The remainder of the
compressed air flows through the annular space between casing 3 and
wall 18 and continues over the outer surface of the liner and a
space between walls 19 and 4, continuing over the inner surface of
the liner. This air provides the film cooling and dilution air for
the combustion apparatus, as is well known.
The rear flanged edges of splitter walls 18 and 19 abut the flanges
24 extending forwardly from liner walls 11 and 12 and terminating
approximately at the plane of forward wall 14. The forward end of
the combustion liner is supported from the combustion case by a
Y-shaped bracket 26 welded or otherwise fixed to the forward wall
14 at the location of each strut 20. The forward end of each
bracket 26 has a radial bore 27 to receive a radial pin 28
extending through a suitable bore 29 in the strut 20, which may be
secured by threads 30 at its inner end. The strut is notched as
indicated at 32 to provide clearance for relative radial expansion
of the liner with respect to the struts and combustion case, which
are normally much cooler in operation of the engine. Thus pins 28
locate the front end of the combustion liner 10 both axially and
radially while allowing radial expansion. Differential expansion
between the air splitter 16 and the combustion liner is permitted
by the freedom for radial sliding movement between the mating edges
of these two parts.
The front wall 14 of the liner has a considerable number of closely
circumferentially spaced inlet arrangements 34 for combustion air
and fuel. These combustion air and fuel arrangements are a feature
of the invention, since they make provision for very thorough
mixing of fuel and air and for introduction of a fuel-air mixture
between radiating flows of air.
Referring to FIGS. 1 and 2, circular or approximately circular
holes 35 are evenly distributed circumferentially around the front
wall 14, preferably at the mean radius of the wall. Hollow bosses
36 which serve as air inlets and distributors are mounted one at
each of the holes 35. The boss 36 is a tubular member folded inside
itself to provide a double-walled structure beginning at an annular
leading edge 38 and terminating at a preferably circular forward
flange 39 and a preferably elliptical rear flange 40. The flange 39
is held against the forward face of wall 14 with some freedom for
motion radially or circumferentially of the combustion apparatus by
two adjacent clips 42 the shape of which is readily apparent from
FIG. 2, the margins of which overlie the flange 39 of the air
distributor. Clips 42 may be spot-welded in place.
The distributor has a ring of air holes 43 in its leading edge so
that air may flow from the space 23 between the walls of the air
distributor and be discharged generally radially outward with some
downstream component, as indicated by the arrow between flange 40
and the inner surface of wall 14. A tubular member 44 mounted
concentrically within the boss 36 defines an air duct 46 for flow
of air into the combustion liner. Tubular member 44 has a mushroom
head 47 flaring from it rather close to the flange 40. In the form
illustrated in FIG. 1, member 44 is supported within the boss 36 by
circumferentially spaced radial pins 48 which may be inserted and
then secured by brazing or otherwise in one of the members. In the
modification illustrated in FIG. 6, the member 44 is supported from
the member 36 by small projections 50 spaced around the upstream
side of head 47 which may be welded to the flange 40. In either
case the air duct 46 is centered in boss 36. The compressed air
entering through the duct 46 is caused to flow outwardly by a
baffle 51 overlying the outlet of the duct, this baffle being
spaced from the flange head 47 by projections 52 on one of these
members welded or brazed to the other.
The annular conduit 54 between the outer surface of member 44 and
the inner surface of boss 36 provides a third entrance into the
upstream end of the combustion chamber between those just
described; that is, that between the wall 14 and flange 40 and that
between flange 47 and baffle 51. This entrance provides for the
admission of fuel with still more combustion air.
The means for introduction of fuel comprises a fuel nozzle 55 of
special type having a bolting flange 56 secured by cap screws 58 or
the like to an annular seat 59 extending from the outer casing 3.
The nozzle has a stem 60 which extends through the casing 3 and
wall 18 and has flanges 62 and 63 to close the openings through
these structures for the entrance to the fuel nozzle into the space
23. As illustrated, the nozzle 55 is of a duplex type having fuel
inlets for small and large fuel flows, respectively. Inlets 64 and
66 communicate with passages defined by a bore 67 through the stem
and a tube 68 mounted within the bore 67, these being isolated from
each other and having separate discharges. The fuel nozzle includes
a tubular nose 70 at the inner end of stem 60 which is mounted
around the tubular member 44 and piloted within the inner surface
of the boss 36 as shown. Nose 70 is spaced from boss 66 by spacing
ridges 71 integral with the end of the nose 70. With the fuel
nozzle bolted in place, the air and fuel entrance parts 36 and 44
are located by it with respect to their position on the front wall
14 of the combustion liner, the flanges 39 being free to slide to
some extent under clips 42.
The fuel passages 67 and 68 discharge into annular manifolds 74 and
75, respectively, which are cast in the nose portion 70 of the fuel
nozzle 55. These manifolds discharge through small orifices or jets
76 and 78, respectively. Preferably, there are four such orifices
distributed equally around the axis of the nose communicating with
each manifold. The result is that, when fuel is supplied through
either or both of the passages 67 or 68, it is discharged through
the ring of jets or nozzles 76 or 78 into the air flowing through
the annular conduits 79 and 54 between the nose 70 and boss 36 and
the tubular member 44.
A circumferential recess 80 on the tubular member provides an
enlargement and then a contraction of the conduit 79, creating
increased turbulence in the air so flowing and furthering the
atomization and uniform mixing of the fuel spray with the air and
small fuel droplet size. Some additional air flows between the
spacing bosses 71 and the total mixture of atomized fuel and air is
discharged through a flaring outlet 82 between the rear flange 40
and the head 47. The fuel thus generally follows the path of the
arrows and is discharged in a radiating sheet which is somewhat
conical with additional air for combustion discharged on both the
upstream and downstream sides of the sheet through the hollow boss
36 on the upstream side and between head 47 and baffle 51 on the
downstream side of the fuel. The result is an intimate mixture of
fuel and air providing for complete combustion in relatively short
space and providing a mixture of combustion products and nitrogen
which is diluted by the air entering through the film air inlets 15
and through dilution holes (not shown) as is customary.
To recapitulate, it will be seen that the forward end of the
combustion liner is very effectively and simply mounted by the
brackets 26 to the combustion case with an arrangement which
provides freedom for expansion of the hotter and cooler parts of
the combustion apparatus. The arrangement for admission of air and
fuel is movably mounted in the front of the combustion liner and
located by the fuel nozzles 56 which are mounted on the combustion
outer case 3. The general arrangement for admission of fuel and air
at the front end of the combustion liner is of a simple,
trouble-free, and practical nature and is readily installed and
removed. It provides an intimate mixture of rapidly-flowing
radiating air sheets with a fuel-bearing sheet sandwiched between
two sheets of air only.
The detailed description of the preferred embodiment of the
invention for the purpose of explaining the principles thereof is
not to be considered as limiting or restricting the invention,
since many modifications may be made by the exercise of skill in
the art.
* * * * *