GB2034875A - Combustion chamber for a gas turbine engine - Google Patents
Combustion chamber for a gas turbine engine Download PDFInfo
- Publication number
- GB2034875A GB2034875A GB7936447A GB7936447A GB2034875A GB 2034875 A GB2034875 A GB 2034875A GB 7936447 A GB7936447 A GB 7936447A GB 7936447 A GB7936447 A GB 7936447A GB 2034875 A GB2034875 A GB 2034875A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flame tube
- combustion chamber
- holes
- combustion
- flame
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 52
- 239000000446 fuel Substances 0.000 claims abstract description 11
- 229910010293 ceramic material Inorganic materials 0.000 claims abstract description 7
- 238000002156 mixing Methods 0.000 claims abstract description 7
- 238000006243 chemical reaction Methods 0.000 claims description 6
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 4
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 4
- 238000000462 isostatic pressing Methods 0.000 claims description 2
- 238000011144 upstream manufacturing Methods 0.000 claims 2
- 238000010276 construction Methods 0.000 claims 1
- 239000000919 ceramic Substances 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 11
- 238000001816 cooling Methods 0.000 description 6
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000003190 augmentative effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000003763 carbonization Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000003134 recirculating effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
Classifications
-
- 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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- 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
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
Abstract
A combustion chamber for a gas turbine engine comprises a heat- resistant ceramic flame tube (2) arranged within a cylindrical outer casing (1) with an annular space (7) therebetween. Combustion and mixing air is supplied to the flame tube (2) via the space (7) and holes (8, 9, 10, 11) in the flame tube arranged such that during combustion the flame front will expand continuously over and along the flame tube with increasing fuel flow. Preferably, the holes are arranged in axially-spaced circumferential rows, the holes in each circumferential row being arranged in diametrically-opposed pairs. The outer casing (1) may also be formed from heat-resistant ceramic material. <IMAGE>
Description
SPECIFICATION
Combustion chamber for a gas turbine engine
The present invention relates to a combustion chamber for a gas turbine engine, comprising a flame tube arranged within a substantially cylindrical outer casing with an annular space therebetween, so that the flame tube may be supplied with combustion air and mixing air through the annular space and holes in the flame tube.
Conventional combustion chambers incorporate a hot primary zone in which the fuel will burn almost completely over the entire operating range. The mixing zone downstream of the primary zone serves to lower rapidly the temperature of the hot gas to temperatures safeiy sustained by the downstream, normally-cooled turbine blades without mechanical damage.
Owing to the high combustion temperatures in the primary zone and subsequent cooling in the mixing zone, a steep temperature gradient occurs between the two zones. While with metallic combustion chambers this temperature gradient is safely accommodated by the ability of the ductile material to expand, it causes conventional ceramic combustion chambers to fail because of the notorious brittleness of the ceramic material.
An object of the present invention is to provide a combustion chamber in which the steep temperature gradient along the wall of flame tube or combustion chamber is avoided, particularly also with increasing or aiternating combustionchamber load.
The invention provides a combustion chamber for a gas turbine engine comprising a flame tube arranged within a substantially cylindrical outer casing with an annular space therebetween so that the flame tube may be supplied with combustion air and mixing air through the annular space and holes in the flame tube, wherein the flame tube is formed from a highly heat-resistant ceramic material, is axially symmetrical and flares in a downstream direction, and the holes in the flame tube are arranged in axially-spaced circumferential rows so that during combustion the flame front will expand continuously over and along the flame tube with increasing fuel flow.
Thus a sharply delineated primary zone is avoided, and the flame front can expand uniformly with increasing combustion chamber load, i.e., with rising fuel flow.
While combustion is here stabilized conventionaily by recirculating swirls, it still propagates uniformly in the entire volume of the flame tube or combustion chamber. Inasmuch as the hole arrangement and the configuration of the combustion chamber is selected such that with increasing fuel flow the flame front can expand in volume, the hot gas temperature, while being different in levei both at idling and at full load, will still remain uniform along the combustion chamber. Inasmuch as the hot gas temperature profile will determine the profile of the wall temperature, a uniform wall temperature without steep gradient along the wall of the flame tube or combustion chamber casing will occur.
An embodiment of the invention will now be described with reference to the accompanying drawing, which illustrates a combustion chamber in longitudinal section.
In the drawing, a combustion chamber essentially comprises an outer casing 1 in which a conical flame tube 2 is inserted and radially spaced therefrom so as to form an annular space 7 therebetween.
The annular space 7 is charged with compressor air from a gas turbine engine (not shown) via air ducts 5 and 6, and respective inlet ports 3 and 4. If desired, the compressor air may be supplied to the combustion chamber in a preheated condition by extracting heat from the turbine exhaust-gas flow in an exhaust-gas heat exchanger.
The space 7 communicates with the interior of the flame tube 2 through four circumferential rows of holes 8, 9, 10 and 1 reading from left to right in the drawing.
As is apparent from the drawing the flame tube 2 is an axially symmetric member flaring in the direction of the main stream. The circumferential rows of holes 8, 9, 10, 11 are designed and arranged such that the reaction volume (preferably also with respect to augmenting fuel flow) can propagate continuously over or along the flame tube 2.
The flame tube 2 is made of a highly heatresistant ceramic material.
The circumferential rows of holes of the flame tube 2 are advantageously designed and arranged such that at least three successive reaction zones
I, II, Ill are formed. The volume of air to be supplied to the mixing zone M is furnished in equal amounts by the circumferential row of holes 10 and by the circumferential row of holes 11.
As is shown for the circumferential row of holeS 8 for the reaction zone I, the holes of each circumferential row are equally distributed over the circumference of the flame tube 2 such that the holes are arranged in diametrically-opposed pairs. Thus, in each circumferential row of holes colliding air streams L are produced inside the flame tube 2, so that about half the air admitted through each circumferential row of holes will flow in the flame tube in an opposite direction to that of the main stream in the combustion chamber (arrows 0), while the other half (arrows
P) of the total air admitted will flow in the flame tube in the same direction of the main stream in the combustion chamber. Reaction eddies W are formed in the reaction zone I.
The requirement for a uniform wall temperature of the flame tube 2 or of the combustion chamber is additionally satisfied by the fact that the holes of two adjacent circumferential rows, e.g. 8 and 9, are staggered in a preferably consistent pattern.
If desired, both the outer casing 1 and the flame tube 2 may be manufactured from a highly heatresistant ceramic material.
If desired, the ceramic flame tube 2 and/or the ceramic outer casing 1 of the combustion chamber may be manufactured from infiltrated
SiC (silicon carbide) as well as by isostatic pressing. This provides special benefits especially resistance of the combustion chamber to thermal shock.
As is also apparent frorn the drawling, a cylindrical, ceramic pipe member 2' is added to the downstream end of the conical flame tube 2.
An exit cone 12 is arranged in the pipe member 2' so as to direct the combustion gases in the direction of arrows T to a compressor turbine (not shown) of the gas generator of the gas turbine engine.
The combustion chamber head 13 is formed essentially by a plate 1 4 bolted to the outer casing 1. The plate 14 carries an at least partially annularly formed central member 1 5 accommodating a fuel injection nozzle 16 aligned with the longitudinal centre line of the combustion chamber.
A spark plug 17 and a cooling-air injection means 1 8 for cooling metallic parts are arranged on opposite sides of the fuel injection nozzle 1 6.
The nozzle 16, the spark plug 1 7 and the cooling air injector 18 communicate with the flame tube 2 through suitable ports in an intermediate plate 1 9.
Retaining members 20, 21 hold the flame tube 2 to the plate 1 9 carried by the combustion chamber head 13. The metallic parts cooled by the cooling air are, for example, the central member 15, the intermediate plate 19 and the retaining members 21,22.
The smooth-walled conical flame tube 2 of the combustion chamber also eliminates the temperature and stress peaks caused in conventional combustion chambers by sharp corners and bends, and it eliminates the development of local fuel traps causing local overheating as well as carbonization of the fuel and the attendant carbon deposits.
Of the total amount of air supplied to the flame tube 2 through the circumferential rows of holes 8, 9, 10,11, preferably 30% is supplied to the circumferential row of holes 8, 18% to the circumferential row of holes 9, 22% to the cirumferential row of holes 10, and 30% to the circumferential row of holes 11.
The above-described combustion chamber does justice to the properties of ceramic materiais while eliminating the flame tube cooling provisions commonly associated with metallic combustion chambers.
Apart from the air expended for cooling the metallic parts at the head of the combustion chamber or flame tube, the entire amount of air admitted to the flame tube benefits combustion.
Claims (10)
1. A combustion chamber for a gas turbine engine comprising a flame tube arranged within a substantially cylindrical outer casing with an annular space therebetween so that the flame tube may be supplied with combustion air and mixing air through the annular space and holes in the flame tube, wherein the flame tube is formed from a highly heat-resistant ceramic material, is axially symmetrical and flares in a downstream direction, and the holes in the flame tube are arranged in axially-spaced circumferential rows so that during combustion the flame front will expand continuously over and along the flame tube with increasing fuel flow.
2. A combustion chamber as claimed in Claim 1, wherein the circumferential rows of holes of the flame tube are arranged such that at least three successive reaction zones are formed during combustion in the flame tube.
3. A combustion chamber as claimed in claim 1 or 2, wherein the holes in each circumferential row are distributed over the circumference of the flame tube in diametrically-opposed pairs, whereby owing to colliding streams of air from each circumferential row of holes, substantially half the total air supplied will flow upstream of the flame tube and substantially half the total air supplied will flow downstream of the flame tube.
4. A combustion chamber as claimed in claim 1, 2 or 3, wherein the holes of two adjacent circumferential rows are uniformly staggered with respect to each other.
5. A combustion chamber as claimed in any one of claims 1 to 4, wherein the outer casing and the flame tube are both manufactured from a highly temperature-resistant ceramic material.
6. A combustion chamber as claimed in any one of the preceding claims, wherein the flame tube and/or the outer casing are manufactured from infiltrated SiC (silicon carbide) as well as by isostatic pressing.
7. A combustion chamber as claimed in any one of the preceding claims, wherein the flame tube has an open-construction upstream end, where substantially metallic members act as a rear wall of the flame tube.
8. A combustion chamber as claimed in claim 7, wherein the metallic parts of the flame tube are arranged to be cooled with air tapped directly at the compressor exit.
9. A combustion chamber as herein described with reference to the accompanying drawing.
10. A gas turbine engine comprising a combustion chamber as claimed in any one of the preceding claims.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19782845588 DE2845588A1 (en) | 1978-10-19 | 1978-10-19 | COMBUSTION CHAMBER FOR GAS TURBINE ENGINES |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2034875A true GB2034875A (en) | 1980-06-11 |
Family
ID=6052606
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB7936447A Withdrawn GB2034875A (en) | 1978-10-19 | 1979-10-19 | Combustion chamber for a gas turbine engine |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS5556530A (en) |
| DE (1) | DE2845588A1 (en) |
| FR (1) | FR2439362A1 (en) |
| GB (1) | GB2034875A (en) |
| IT (1) | IT1162785B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106247402A (en) * | 2016-08-12 | 2016-12-21 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of burner inner liner |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3031689A1 (en) * | 1980-08-22 | 1982-03-04 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | CERAMIC COMBUSTION CHAMBER |
| JPS58133526A (en) * | 1982-02-03 | 1983-08-09 | Kenji Watanabe | Hydrogen gas turbine engine |
| JPH0619963Y2 (en) * | 1985-10-16 | 1994-05-25 | 日産自動車株式会社 | Combustor assembly structure |
| DE4223828A1 (en) * | 1992-05-27 | 1993-12-02 | Asea Brown Boveri | Method for operating a combustion chamber of a gas turbine |
| DE4222391C2 (en) * | 1992-07-08 | 1995-04-20 | Gutehoffnungshuette Man | Cylindrical combustion chamber housing of a gas turbine |
| DE19536706A1 (en) * | 1995-10-02 | 1997-04-03 | Lbe Beheizungseinrichtungen | Jacketed radiant heating tube e.g. for industrial furnace |
| CN101881444B (en) * | 2010-06-02 | 2012-07-04 | 北京北机机电工业有限责任公司 | Flame copying cylinder, surface burner and fuel oil heater |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR962862A (en) * | 1946-10-26 | 1950-06-22 | ||
| US2974485A (en) * | 1958-06-02 | 1961-03-14 | Gen Electric | Combustor for fluid fuels |
| US3918255A (en) * | 1973-07-06 | 1975-11-11 | Westinghouse Electric Corp | Ceramic-lined combustion chamber and means for support of a liner with combustion air penetrations |
| US3880575A (en) * | 1974-04-15 | 1975-04-29 | Gen Motors Corp | Ceramic combustion liner |
| US3990231A (en) * | 1974-10-24 | 1976-11-09 | General Motors Corporation | Interconnections between ceramic rings permitting relative radial movement |
| US4030875A (en) * | 1975-12-22 | 1977-06-21 | General Electric Company | Integrated ceramic-metal combustor |
| US4008568A (en) * | 1976-03-01 | 1977-02-22 | General Motors Corporation | Combustor support |
-
1978
- 1978-10-19 DE DE19782845588 patent/DE2845588A1/en active Pending
-
1979
- 1979-10-17 FR FR7925752A patent/FR2439362A1/en not_active Withdrawn
- 1979-10-18 IT IT26595/79A patent/IT1162785B/en active
- 1979-10-18 JP JP13505979A patent/JPS5556530A/en active Pending
- 1979-10-19 GB GB7936447A patent/GB2034875A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106247402A (en) * | 2016-08-12 | 2016-12-21 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of burner inner liner |
| CN106247402B (en) * | 2016-08-12 | 2019-04-23 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of burner inner liner |
Also Published As
| Publication number | Publication date |
|---|---|
| IT1162785B (en) | 1987-04-01 |
| DE2845588A1 (en) | 1980-04-24 |
| JPS5556530A (en) | 1980-04-25 |
| FR2439362A1 (en) | 1980-05-16 |
| IT7926595A0 (en) | 1979-10-18 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |