US2741090A - Combustion equipment for gas-turbine engines with anticarbon wall portion - Google Patents
Combustion equipment for gas-turbine engines with anticarbon wall portion Download PDFInfo
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- US2741090A US2741090A US154965A US15496550A US2741090A US 2741090 A US2741090 A US 2741090A US 154965 A US154965 A US 154965A US 15496550 A US15496550 A US 15496550A US 2741090 A US2741090 A US 2741090A
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- wall portion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Description
April 10, 1956 F. M. JOHNSON COMBUSTION EQUIPMENT FOR GAS-TURBINE ENGINES WITH ANTICARBON WALL PORTION 5 Sheets-Sheet 1 Filed April 10, 1950 INYENTOR FRANCIS r1 a'ouusou MM; WQHKZ I Arra/ZNEYS l/ Aprll 10, 1956 JOHNSON 2,741,090
COMBUSTION EQUIPMENT FOR GAS-TURBINE ENGINES WITH ANTICARBON WALL PORTION Filed April 10, 1950 5 Sheets-Sheet 2 INVEA/TUR FRANCIS M. JOHNSON April 10, 1956 F. M. JOHNSON 2,741,090
COMBUSTION EQUIPMENT FOR TU INE ENGINES WITH ANTICARBON w PO 0N Filed April 10, 1950 v 3 Sheets-Sheet 3 mm m F. MJ OHNSON l; l/w w awn United States Patent D COMBUSTION EQUIPMENT FOR "GAS-TURBHQE ENGINES WITH AYTICARBQN WALL PORTEQN Francis Murray Johnson, Sireatham, London, England, assignor to Rolls-Royce Limited, Derby, England, a Britishcompany Application April 19, 1951}, Serial No. 154365 Claims priority, applicationGrcat Britain dune :30, U4)
8 Claims. {CL 69- 3165) This invention relates tocombustion equipment for gasturbine engines. "It-is concernedwith combustion equipment of the kind comprising afiame tube accommodated Within an air casing, so as to provide a passage between the outer-wall of the flametube and the air-casing through which air passes before being introduced into the flame tube through suitable apertures or entry ducts, andwherein primary air is introduced at the inlet end of the flame tube. In combustion equipment of this kind there are at least two distinct supplies of air into the interior of the flame tube, referred to as primary air, with whichcombustion of the fuel is initiated, and mixing air, which is introduced mainly to-dilute the combustion gases and to coolthern. The mixing airmay also assist thecomp'l'e- 'tion of combustion.
It has hitherto been the practice in combustion equipment of the kind specified, to provide fuel injection'means at the inlet end of the flame tube to introduce a spray of atomized'liquid fuel into the flame tube and to introduce primary air into the flame tube through-a perforated baffle, or swirling device which surrounds the fuel injection means. Certain such arrangements have included a 'wall portion of the'flame tube at'its in'let-endwhich isdivergent in the direction of the flow-of air 'therethroug'h.
It has been found in practice that withzsuch lcnownarrangements there -is a tendency for the formation of a carbon deposit on the perforated baflle or swirl device through which the primary air-is introduced and/oron-the divergent wall portion, which deposit adversely ait'ectstl'ic metering-of the primary air. into the combustion chamber. As a result, deterioration of combustion efliciency 'has *occu'rred, adversely 'afiecting the operation'o'f the engine.
The primary-object 'of' the present invention -'is to reduce or obviate the tendency forcar'bon to be'deposited on 'the flame tube parts in the region of introduction of=prirnary air, whereby such undesirable deterioration of combustion e'fiiciency is avoided.
According to'the present invention, in cornbustion equipment of the kind specified for gas-t-urbine engines, the flame tube has, at its inlet end, a wall portion which is divergent in the direction of the flow of air'through the flame tube, which wall portion constitutes part of the boundary surface of the space Within the flame tube, and has supported adjacent to the wall portion an annular-part of divergent substantially 'frusto-conicalflform located'so as to constitute with the wall portion an annular channel through which a major-parrot the flow of primary air is introduced into the flame tube, the primary air emerging from the channel alongthe inner surface of the wall portion.
Adoption of the invention provides that the main flow ofprimary-air into the flame tube takes place along the surface oftheldivergent wall'portion, to sweeppthis surface Preferably the cross-sectional area of the channel in the 2,741,090 Patented Apr. '10, 1-956 direction of airflow therethroug'h-is convergent toproduee an acceleration of flow and thus to increase the scouring action of the primary air flow along't-he surface of the divergent wall portion.
The invention is applicable to one type of combustion equipment of the kind specified in which there-are a plurality of flame tubes of tubular form accommodated each within a separate tubular air casing, so that the gap 'between the wallof-the flame tube and the air "casing is of annularsection. 7
The invention is also applicableto'another type of combustioncquipment of the kindspecified in whichthe flame tubes are of tubular form and are accommodated "within an air casing of annular construction, so that ap'lurality or flame tubes are accommodated in asingle annular air casing.
A third type of combustion equipment of the kind-specitied to which the invention is applicable is that in which the flame tube is itself of annular form, accommodated within an annular air casing.
in applying the present inventionto combustion equipof the first and second types mentioned, one ,preferred construction provides a divergent Wall portion-and annular part which are both of divergent tubular form, the divergent wall portion being connected to the inlet end 0t the main-wall portion of the flame tube, and the annular' part being supported internally of the divergent-wall portion to provide an annular channel for the passage of primary air into the flame tube. In such an arrangement uelinjection means may be provided concentrically-within the annular part to introduce atomized :or'vaporized fuel into-the flameatube at-its'irilet end.
In applying the invention to the third type of combustion equipment mentioned oneprefferred constructionprovides a first divergent wall portion 'whic'h'is attached 'to theinlet end of the main portion of an outer defining Wail of the annular-flame tube, Whilea second wall portionfis attached to the inlet end of the mairrportion of the inner defining'wall of-the annular-flame tube, the twowall'portions together defining a space between the inner and'out er walls 'of thefiarnetube'which is divergent in the direction of the flow of air through the fiametube; likewise an annular part ;is associated'with each of the wall portions mentioned, so that inner and outer annular channels are constituted for the passage 'o'f prirnary air' into 'theiinterinr of the flame tube. With such .an arrangement a series-of fuel injection means are conveniently located circumferentially in'the annulus "between 'the 'two annular parts to introduce fuel in'atomized or vaporized form toiflieicombustion chamber.
According to a feature of this invention a subsidiary flow of primary air may be introduced into the flame tube in the region :of the transverse plane through the flame "tube approximately containing the downstream and of the annular ringpart or parts. Thus in the case of'the firstand second types .of combustion equipment mentionedsuchsubs'idiaryflow mayibe introduced through an annular area between the fuel injectionmeans and the downstream end of the annular part, While in "the case of the third type of combustion eouiprnentmentioned the subsidiary flow *may be introduced through an annular area between the .two annular. parts. Preferably "such subsidiary 'air'is "supplied to the interior of the'flametubewith a degree of swirl given it by swirl vanes which, due to the tangential velocity component of the subsidiary flow of primary air, are efliciently scoured to reduce the tendency for carbon to deposit thereon.
Aifurther feature of'theinvention provides for a further -.subsidiary:flow .of primary air between :the 1 fuel injection means-and :the flame tube at :itSinlet end.
In arrangements of combustion equipment according to the present invention the supply of primary air to the inlet end of the frame tube is preferably effected from the engine compressor through a divergent entry duct, which may be formed integrally with the flame tube or which of air in the delivery duct so that some of it passes into the'divergent duct while the remainder passes externally thereof and thence into the space between the flame tube and air casing, whence it passes into the interior of the flame tube as mixing air. The divergent entry duct may include an internal duct-defining liner connecting at its downstream end'with the inlet end of the divergent wall portion of the flame tube.
Fig. 3 shows a modified form of gas turbine engine to' which the invention is applicable,
Fig. 4 shows a further modified form of gas turbine engine in accordance with the invention, and Figure 5 is a perspective view from within the combustion space looking on the fuel injection device.
The gas turbine engine of Fig. 1 comprises a compressor delivering compressed air to combustion equipment 11, from which the products of combustion pass through a turbine 12 which drives the compressor 10, and thence through a jet pipe 13 having a propelling nozzle 14, to atmosphere. The engine is suitable for aircraft jet propulsion.
The combustion equipment 11 comprises a plurality of substantially tubular flame tubes within substantially tub ular air casings. One such air casing and flame tube is is of generally cylindrical form, the axis of which lies on the axis of the flame tube. The fuel injection means may be as described in U. S. Patent No. 2,700,416 which issued on January 25, 195 5 where provision is made to prevent or reduce the tendency to carbon formation on the I orifice part or parts of the fuel injector.
shown in section in Fig. 2, the arrangement comprising an entry expansion chamber portion 15 which is connected with the delivery of the engine compressor 10 and is of divergent substantially circular cross-section. The expansion chamber 15 is connected by a bolted flange joint 16 with a tubular main air casing part 17 which in turn is connected at its outlet end with a nozzle entry assembly of the turbine 12. Internally of the air casing 17 there is accommodated a generally tubular flame tube 18; The flame tube 18 is spaced from the Wall of the into the expansion chamber 15 and provides a passage for the flow of mixing air into the flame tube. 7
Within the expansion chamber 15 is mounted aduct air casing 17 and into a primary air flow which passes through the divergent entry duct 20a into the interior of the flame tube '18 at its entry end. The divergent entry duct part 20 is also formed at its downstream end 20c with a spigot flange 21 which serves to support the flame tube 18, so that the entry duct 20 is in effect an extension of the flame tube 18 into the expansion chamber 15.-
Fuel injection means 22 is supported on the axis of the flame tube in the plane of the exit end of the divergent entry ductpart 20, being conveniently carried on a boss 23 by a number of legs 24 (one only of which is shown 1 in the drawing) cast integrally with the entry duct part air casing 17 to form an annular duct 19 which extends.
part-20, defining adivergent entry duct 20a, the smaller The inlet end of the flame tube is of double skin formation, the outer skin 25 of which provides the socket for the spigot 21 on the divergent entry duct part 20, and the inner skin 26 of which is spaced inwardly of the divergent entry duct part 20, to constitute'a divergent annular wall portion of the flame tube. This portion spigots at its inlet end 26:: in an annular socket 27 on a sheet-metal liner 28 within the divergent entry duct 20a. At its outer end 26b the divergent wall portion 26 connccts with a substantially cylindrical main portion of the flame tube 18. Within the divergent wall portion 26 an annular ring 29 of divergent, substantially frustoconical form is provided, which ring is of less axial length and less maximum diameter than the divergent wall portion 26 of the flame tube. The ring 29 is located so as to provide, with the divergent wall portion 26, an annular channel 39 which converges from its inlet end 30a, which end lies substantially in the plane of the exit end Ziic of the divergent entry duct 20a to receive air therefrom, to its outlet end 39b which lies adjacent the divergent face of the inner wall 26. The ring 29 is spaced from the inner skin 26 by means of tubular spacer members 31, and is supported by bolts 32 which conveniently pass through the spacer members 31.
tially without swirl, in a direction parallel to the surface of the divergent wall portion 26 so as to scour this surface.
A sleeve 33 surrounding the fuel injector 22 is supported within the ring 29 by a number of swirl vanes 34. The latter (see Figure 5) are so shaped and disposed relative to one another as to provide passages for a subsidiary flow of primary air which at entry are substantially axial i. e. the entry areas face upstream into the divergent .entry duct, while at exit the passages 35 direct the air flow with a considerable tangential component of velocity into the flame tube 18. Further the passages 35 between the vanes 34 are convergent 'so that relatively high exit velocity is obtained preventing or reducing the tendency for carbon to be deposited on the exit surfaces of the vanes 34. A further annu-- takes place through the annular channel 30 defined between the divergent wall portion 26 of the flame tube and the .ring 29 associated therewith, while comparatively minor subsidiary flows of primary air take place through the swirl vane passages 35 and through the annular passage 36 surrounding the fuel injector 22.
These flows of primary air will reduce or obviate the" tendency for carbon to be deposited on the flame tube parts in the region of introduction of primary air.
Y A modified form of gas turbine engine to which the invention'is applicable is shown in transverse cross section in Fig. 3. In this arrangement the combustion equipment 11a comprises a plurality of flame tubes 18 accommodated in a single annular air casing 117, which 20. The fuel injection means 22 may be of any known or convenient kind, and is preferably of the kind injecting liquid fuel as an atomized spray through an atomizing orifice. The fuel injection means 22 in this embodiment to such an arrangement.
is co-axial with the compressor 10 and the turbine 12 of the engine. It will be appreciated that the construction according to the invention. may be readily applied Each flame tube 18 will be i identical with those of the embodiment already described,
as will be the divergent entry duct part 20 corresponding with each flame tube. The annular air casing 117 comprising an inner member 117a and an outer member 117b is bolted to an annular expansion chamber of divergent cross sectional area in the-direction of the flow of air.
A further modified form of gas turbine engine to which the invention is applicable is shown in transverse cross section in Eig. 4. In this arrangement, combustion equipment 11b comprises a single annular flame tube 218 accommodated in a single bar casing 217, both of which are co-axial with the compressor 16 and the turbine 12 of the engine. The construction according to the invention may also be readily applied to this arrangement, as will be appreciated. Each flame tube 218, while being identical with that of the first embodiment above described in longitudinal cross section, will extend circumferentially to form a continuous annular duct. The inner member 217:: and the outer member 217k of the annular air casing 217 will be bolted to an annular expansion chamber of divergent cross-sectionm area in the direction of the flow of air. The divergent entry duct part 29 will support the inlet end of the annular flame tube 218.
I claim:
1. Combustion equipment for a gas-turbine engine comprising an air casing and a flame tube accommodated in said air casing and defining a combustion space Within said flame tube, said flame tube having an imperforate inlet wall portion curved away from said combustion space and bounding a duct through which air flows into said flame tube, a first part of said inlet wall portion being convex toward said combustion space, and a second part of said inlet wall portion immediately downstream of said first part being frusto-conical and bounding the combustion space and being divergent with respect to said flow of air whereby carbon formation is liable to occur on said second part, and a further wall portion which is adjacent said inlet wall portion, is curved away from said combustion space and .is located on the side of said inlet wall portion adjacent said combustion space, said further wall portion being at least in part convex toward said combustion space, said further wall portion and said inlet wall portion affording between the inlet wall portion andithe whole length of the further wall portion an annular channel curved away from said combustion space, and said second part of the inlet wall portion being substantially Wholly beyond the downstream end .of said further wall portion, whereby air entering the combustion space through said channel passes along the surface of said second part of the inlet wall portion, whereby carbon formation on said second part is substantially reduced.
2. Combustion equipment for a gas-turbine engine comprising an air casing and a flame tube accommodated in said air casing and defining a combustion space within said flame tube, said flame tube having an imperforate inlet Wall portion curved away from said combustion space and bounding a duct through which air flows into said flame tube, a first part of said inlet wall portion being convex toward said combustion space, and a second part of said inlet wall portion immediately downstream of said first part being frusto-conical and bounding the combustion space and being divergent with respect to said flow of air whereby carbon formation is liable to occur on said second part, and a further wall portion which is adjacent said inlet wall portion is curved away from said combustion space and 'is located on the side of said inlet wall portion adjacent said combustion space, said further wall portion being at least in part convex toward said combustion space, and said further wall portion lying nearer to said inlet wall portion at its downstream end than at its upstream end thereby to define between the inlet wall portion and the whole length of the further wall portion an annular channel which is curved away from said com- 6 bustion space and which converges from its inlet end to its outlet end, and said second part of the inlet wall portion being substantially wholly beyond the downstream end .of said further wall portion, whereby air entering the combustion space through said channel passes along the surface of said second part of the inlet wall portion, whereby carbon formation on said second part is substantially reduced.
3. Combustion equipment for a gas-turbine engine comprising a tubular air casing and a tubular flame tube accommodated in said air casing and defining a combuslion space within the flame tube, said flame tube having an imperforate-inlet wall portion curved away'from said combustion space towards the air casing and formed substantially as .a body .of revolution bounding aduct through which air flows intovsaid flame tube, a first part of said inlet wall portion being convex toward said combustion space, and a second part of said inlet Wall portion immediately downstream .of said first part being frustoconical and bounding the combustion space and being divergent with respect to saidflow of air whereby carbon formation .is liable to occur on said second part, and a further wall portion which is adjacent said inlet wall portion, is curved away from said combustion space, and
is located on the side of said inlet wall portion adjacent said combustionspacm'said further Wall portion being at least in part convex toward said combustion space, said further wall portion and said inlet wall portion affording between the inlet wall portion and the whole length of the further wallportion an annular channel curved away from said combustion space and'said second part of the inlet wall portion being substantially wholly beyond the downstream end .ofsaid further wall portion whereby air entering the combustion spacethrough said channel passes along the surface of saidsecond part of the inlet wall portion, wherebytcarbon formation on said second part is substantially reduced.
4. Combustion equipment for a gas-turbine engine comprising a tubular air casing and a tubular flame tube accommodated in said air casing and defining a combustion space within said flame tube, said flame tube having an imperforate inlet :wall portion curved away from said combustion space toward the air casing and formed subvstantially as a body of revolution bounding a duct through which air flows into said'fiame tube, a first part of said wall portion being convex toward said combustion space,
and a second part of said wall portion immediately downstream of said first-partbeing frusto-conical and bounding the combustion space and being divergent with repect to said fiow of air whereby carbon formation is liable to occur on said :second part, and a further wall portion which is adjacent said inlet wall portion, is curved away from said combustion space and is located on the side of said inlet wall portion adjacent said combustion space, said further wall portion being at least in part convex toward said combustion space, and said further wall portion lying nearer to said inlet wall portion at its downstream end than at its upstream end thereby to define between the inlet wall portion and the whole length of the further wall portion an annular channel which is curved away from said combustion space and which converges from its inlet end to its outlet end, and said second part of the inlet wall portion being substantially wholly beyond the downstream end of said further wall portion, whereby air entering the combustion space through said channel passes along the surface of said second part of the inlet wallportion, whereby carbon formation on said second part is substantially reduced,
'5. Combustion equipment :for a gas-turbine engine comprising an annular air casing having an inner annular wall and an outer annular wall, and a plurality of tubular flame tubes accommodated in said air casing and defining a combustion space within each of said flame tubes, each of-said flame tubes having an imperforate inlet wall portion curved away from said combustion space and formed part is substantially reduced.
carbon formation is liable to occur on said second part,
and a further wall portion which is adjacent said inlet wall portion is curved away fiom said combustion space and is located on the sideof said inlet wall portion adjacent said combustion space, said further wall portion being at least in part convex toward said combustion space, said further wall portion and-said inlet wall portion aifording between the inlet wall portion and the a whole length of the further wall portion an annular channel curved away from said combustion space, and said second part of the inlet wall portion being substantially wholly beyond the downstream end of said further wall portion, whereby air entering the combustion space through said channel passes along the surface of said second downstream part of the inlet wall portion, whereby carbon formation 'on said second part is substantially reduced. v j
6. Combustion equipment for a gas-turbine engine comprising an annular air casing having an inner annular wall and an outer annular wall, and a plurality of tubular flame tubes accommodated in said air casing and defining a combustion space within each of said flame tubes, each of said flame tubes having an imperforate inlet wall portion curved away from said combustion space and formed substantially as a body of revolution bounding a duct through which air flows into i said flame tube, a first part of said inlet wall portion being convex toward said said combustion space, and a second part of said inlet wallportion immediately downstream of said first part being frusto-conical and bounding the combustion space and being divergent with respect to said flow of air whereby carbon formation is liable to occur on said wall portion adjacent said combustion space, said further 1 wall portion being at least in part convex toward said combustion space, and said further wall portion lying nearer to said inlet wall portion at its downstream end than at its upstream end thereby to define between the inlet wall portion and the whole length of the further wall portion an annular channel which is curved away from said combustion space and which converges from its inlet end to its outlet end, and said second part of the inlet walllportion being substantially Wholly beyond the'downs'trearn end of said further wall portion, whereby air entering the combustion space through said channel passes along the surface of said second part of the inlet wall portion, whereby carbon formation on said second 7. Combustion equipment for a gas-turbine engine comprising an annular air casing having an inner annular wall and an outer annular wall, and an annular flame tube accommodated in said air casing and having an inner annular flame tube wall and an outer annular flame tube wall spaced from the respective air casing walls and defining a combustion space between the flame tube walls, said flame tube havingan imperforate inner inlet Wall portion and an imperforate outer inlet Wall portion, each part of said inner inlet wall portion immediately down stream of said first part being frusto'conical and bounding the combustion space and extending inwardly. from the first part towards the inner air casing wall ,whereby carbon formation is liable to occur on said second part, and a further inner wall portion which is, adjacent said inner inlet wall portion, is curved away from said combustion space and is located on the side ofsaid inner inlet wall portion adjacent said combustion space, said further inner wall portion being at least in part convex toward said combustion space, said further inner Wall portion and said inner inlet wall portion aftording between the inner inlet wall portion and the whole length of the further inner wall portion a first annular channel curved away from said combustion space, and said second part of the inner inlet wall portion being substantially wholly beyond the downstream end of said further inner wall portion, whereby air entering the combustion space through said first annular channel passes along the ,surface of said 7 second part of the inner inlet wall portion and carbon formation on said second part is substantially reduced,
'said imperforate outer inlet wall portion having aifirst part which is convex towards the combustion space and,
a second part which is immediately downstream of said first part of the outer inlet wall portion and is frustoconical and extends outwardly from the first part towards the outer air casing wall whereby carbon formation is liable to occur thereon, a further outer wall portion which is adjacent said outer inlet wall portion, is curved away from said combustion space and is located on the side of said outer inlet wall portion adjacent said combustion space, said further outer wall portion being at least in part convex toward saidcornbustion space, said further outer wall portion and said outer inlet wall portion afiord ing between the outer inlet wall portion and the whole length of the further outer wall portion a second annular comprising an annular aircasing having an inner annular wall and an outer annular Wall, and an annular flame tube accommodated in said air casing and having an inner annular flame tube wall and an outer annular flame tube wall spaced from the respective air casing walls and defining a combustion space between the flame tube walls, said flame tube having an imperforate inner inlet wall portion and an imperforate outer inlet wall portion, each of said inlet wall portions being curved away from said combustion space towards the adjacent annular wall of the air casing and being formed substantially as abody of revolution, said inlet wall portions together bounding an air inlet duct through which air flows toward said combustion space, a first part of said inner inlet wall portion being convex toward said combustion space, and a second part of said inner inlet wall portion, immediately downstream of said first part being frusto-conical and bounding the combustion space and extending inwardly from the first part towards the inner air casing wall wherea by carbon formation is liable'to occur on said second part, and a further inner'wall'portionwhich is adjacent said inner inlet wall portion, is curved away from said combustion space and is located on the side of said inner inlet wall portion adjacent said combustion space, said further inner wall portion beingat'le'ast'in part convex toward said combustionspace, said further innerwall' portion lying nearer to said inner inlet wall portion at its downstream end than atits 'upstre'am' end thereby to define between the inner inlet wall portion and the whole length of the further innerwall portion "a first annular channel curved away from said'combu'stion space, and said second part of the inner inlet wall portion being substantially wholly beyond the downstream end of said further inner wall portion, whereby air entering the combustion space through said first annular channel passes along the surface of said second part of the inner inlet wall portion and carbon formation on said second part is substantially reduced, said imperforate outer inlet wall portion having a m st part which is convex towards the combustion space and a second part which is immediately downstream of said first part of the outer inlet wall portion and is frusto-conical and extends outwardly from the first part towards the outer air casing wall whereby carbon formation is liable to occur thereon, a further outer wall portion which is adjacent said outer inlet wall portion, is curved away from said combustion space and is located on the side of said outer inlet wall portion adjacent said combustion space, said further outer wall portion being at least in part convex toward said combustion space, said further outer wall portion lying nearer to said outer inlet wall portion at its downstream end than at its upstream end thereby to define between the outer inlet wall portion and the whole length of the further outer wall portion a second annular channel curved away from said combustion space, and said second part of the outer inlet wall portion being substantially wholly beyond the downstream end of said further outer wall portion, whereby air entering the combustion space through said second annular channel passes along the surface of said second part of the outer inlet Wall portion and carbon formation on said second part is substantially reduced.
References (Iited in the file of this patent UNITED STATES PATENTS 1,316,021 Doble Sept. 6, 1919 1,434,406 Purnell Nov. 7, 1922 2,445,114 Halford July 13, 1948 2,547,619 Buckland Apr. 3, 1951 2,560,207 Berggren et a1 July 10, 1951 2,616,257 Mock Nov. 4, 1952 2,618,928 Nathan Nov. 25, 1952 2,627,721 Rosenlund Feb. 10, 1953 2,638,745 Nathan May 19, 1953 2,664,702 Lloyd et a1 Jan. 5, 1954 FOREIGN PATENTS 579,424 Great Britain Aug. 2, 1946
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB17383/49A GB694484A (en) | 1949-06-30 | 1949-06-30 | Improvements relating to combustion equipment for gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2741090A true US2741090A (en) | 1956-04-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US154965A Expired - Lifetime US2741090A (en) | 1949-06-30 | 1950-04-10 | Combustion equipment for gas-turbine engines with anticarbon wall portion |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US2741090A (en) |
| GB (1) | GB694484A (en) |
Cited By (4)
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|---|---|---|---|---|
| US2890569A (en) * | 1954-05-03 | 1959-06-16 | Phillips Petroleum Co | Removal of carbon deposits in jet engines |
| US2907171A (en) * | 1954-02-15 | 1959-10-06 | Lysholm Alf | Combustion chamber inlet for thermal power plants |
| US3018624A (en) * | 1954-03-02 | 1962-01-30 | Bristol Siddeley Engines Ltd | Flame tubes for use in combustion systems of gas turbine engines |
| US3092964A (en) * | 1954-03-30 | 1963-06-11 | Martin Peter | Method of relighting in combustion chambers |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL268838A (en) * | 1960-09-13 |
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-
1949
- 1949-06-30 GB GB17383/49A patent/GB694484A/en not_active Expired
-
1950
- 1950-04-10 US US154965A patent/US2741090A/en not_active Expired - Lifetime
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1316021A (en) * | 1919-09-16 | doble | ||
| US2445114A (en) * | 1948-07-13 | Arrangement of jet propulsion | ||
| US1434406A (en) * | 1921-03-19 | 1922-11-07 | William R Purnell | Air-control register for fuel burners |
| US2638745A (en) * | 1943-04-01 | 1953-05-19 | Power Jets Res & Dev Ltd | Gas turbine combustor having tangential air inlets for primary and secondary air |
| GB579424A (en) * | 1943-09-29 | 1946-08-02 | Lucas Ltd Joseph | Improvements relating to liquid fuel combustion apparatus for generating gases for power purposes |
| US2618928A (en) * | 1944-05-19 | 1952-11-25 | Power Jets Res & Dev Ltd | Combustion apparatus with vaned fuel injector means |
| US2616257A (en) * | 1946-01-09 | 1952-11-04 | Bendix Aviat Corp | Combustion chamber with air inlet means providing a plurality of concentric strata of varying velocities |
| US2627721A (en) * | 1947-01-30 | 1953-02-10 | Packard Motor Car Co | Combustion means for jet propulsion units |
| US2664702A (en) * | 1947-08-11 | 1954-01-05 | Power Jets Res & Dev Ltd | Cooled flame tube |
| US2560207A (en) * | 1948-02-04 | 1951-07-10 | Wright Aeronautical Corp | Annular combustion chamber with circumferentially spaced double air-swirl burners |
| US2547619A (en) * | 1948-11-27 | 1951-04-03 | Gen Electric | Combustor with sectional housing and liner |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2907171A (en) * | 1954-02-15 | 1959-10-06 | Lysholm Alf | Combustion chamber inlet for thermal power plants |
| US3018624A (en) * | 1954-03-02 | 1962-01-30 | Bristol Siddeley Engines Ltd | Flame tubes for use in combustion systems of gas turbine engines |
| US3092964A (en) * | 1954-03-30 | 1963-06-11 | Martin Peter | Method of relighting in combustion chambers |
| US2890569A (en) * | 1954-05-03 | 1959-06-16 | Phillips Petroleum Co | Removal of carbon deposits in jet engines |
Also Published As
| Publication number | Publication date |
|---|---|
| GB694484A (en) | 1953-07-22 |
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