GB812317A - Improvements in combustion chambers for gas turbines and ram-jets - Google Patents

Improvements in combustion chambers for gas turbines and ram-jets

Info

Publication number
GB812317A
GB812317A GB15721/57A GB1572157A GB812317A GB 812317 A GB812317 A GB 812317A GB 15721/57 A GB15721/57 A GB 15721/57A GB 1572157 A GB1572157 A GB 1572157A GB 812317 A GB812317 A GB 812317A
Authority
GB
United Kingdom
Prior art keywords
annular
wall
walls
upstream
flame tube
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.)
Expired
Application number
GB15721/57A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Publication of GB812317A publication Critical patent/GB812317A/en
Expired legal-status Critical Current

Links

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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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

Abstract

812,317. Jet-propulsion plant. LEDUC, R. May 17, 1957 [May 18, 1956], No. 15721/57. Class 110 (3). [Also in Group XII] A combustion chamber assembly for a ramjet unit or a gas-turbine engine comprises a staggered series of annular flame tubes 1, 2 ... 6 of progressively increasing diameter in the downstream direction, the flame tubes being defined by partially-overlapping sleeve-like annular walls 7, 8 . . . 12. Each of these walls has a bell-shaped upstream portion such as 9b which defines the outer boundary of one flame tube 3, and a substantially cylindrical downstream portion 9a which defines the inner boundary of the adjacent flame tube 4. The trailing edge of each wall is substantially in line axially of the assembly with the upstream limit of the cylindrical portion of the adjacent wall lying radially outside it, and the leading edge of each wall is in line with, axially of the assembly, or slightly in advance of the upstream limit of the cylindrical portion of the adjacent wall lying radially inside it. The leading portion of the bell-shaped portion 9b of each annular wall is shaped so as to be approximately cylindrical. The assembly of flame tubes is disposed within an outer casing 26, the propulsion nozzle 25 of a gas turbine jet engine being disposed centrally within the flame tube assembly, the surface of the nozzle 25 forming the inner boundary of the upstream annular flame tube 1. The annular walls 7, 8. . . 12 are supported at their leading edges on longitudinally-extending struts 24. The downstream annular wall 12 is not formed with a cylindrical portion such as 9a. Each annular flame tube 1, 2 . . . 6 is formed at its entry with an annular diffuser 14, and is provided with a flame holder comprising a series of radiallydisposed bars 13 of V-section pointing upstream and possibly also with a ring member 13a of V-section, also with a series of fuel injectors 15. The inner wall of each annular flame tube may be double-walled as shown at 9a, 9d so as to afford an annular passage 16 open at the upstream and downstream ends for the flow of cooling air therethrough and the walls 9a, 9d are perforated as at 17 so that streams of cooling air may pass therethrough. The walls 8a, 8b, 8d, 9a, 9b, 9d may be longitudinally corrugated as shown in Fig. 4, spacer members being disposed at axially-spaced intervals between the walls, each spacer comprising a pair of cylindrical members 21, 22 with a corrugated ring 23 therebetween the parts being bonded together. The wall portions 9a, 9b may be arranged to overlap as indicated at 18, 19 in Fig. 2, so that the boundary layer on the outer surface of the wall portion 9b is sucked off into the outlet of the annular flame tube 3. Alternatively, the wall 9b may be louvred to permit boundary layer removal.
GB15721/57A 1956-05-18 1957-05-17 Improvements in combustion chambers for gas turbines and ram-jets Expired GB812317A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1150640T 1956-05-18

Publications (1)

Publication Number Publication Date
GB812317A true GB812317A (en) 1959-04-22

Family

ID=9647489

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15721/57A Expired GB812317A (en) 1956-05-18 1957-05-17 Improvements in combustion chambers for gas turbines and ram-jets

Country Status (2)

Country Link
FR (1) FR1150640A (en)
GB (1) GB812317A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5341640A (en) * 1993-03-30 1994-08-30 Faulkner Robie L Turbojet engine with afterburner and thrust augmentation ejectors
EP2107309A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Quarls in a burner
EP2107311A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Size scaling of a burner
EP2107310A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Burner
EP2107312A1 (en) 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Pilot combustor in a burner
RU2468298C2 (en) * 2008-04-01 2012-11-27 Сименс Акциенгезелльшафт Stage-by-stage fuel combustion in burner

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2124141B1 (en) * 1971-02-09 1975-02-21 Snecma
FR2587414B1 (en) * 1985-09-17 1987-12-18 Aerospatiale STATOREACTOR HAVING GUIDANCE OF THE AIR-FUEL AND MISSILE MIXTURE PROVIDED WITH SUCH A STATOREACTOR

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5341640A (en) * 1993-03-30 1994-08-30 Faulkner Robie L Turbojet engine with afterburner and thrust augmentation ejectors
EP2107309A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Quarls in a burner
EP2107311A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Size scaling of a burner
EP2107310A1 (en) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Burner
EP2107312A1 (en) 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Pilot combustor in a burner
WO2009121778A1 (en) * 2008-04-01 2009-10-08 Siemens Aktiengesellschaft Quarls in a burner
WO2009121777A1 (en) * 2008-04-01 2009-10-08 Siemens Aktiengesellschaft Burner
WO2009121781A1 (en) * 2008-04-01 2009-10-08 Siemens Aktiengesellschaft Pilot combustor in a burner
WO2009121776A1 (en) * 2008-04-01 2009-10-08 Siemens Aktiengesellschaft Size scaling of a burner
CN101981379B (en) * 2008-04-01 2012-06-20 西门子公司 Size scaling of a burner
RU2455570C1 (en) * 2008-04-01 2012-07-10 Сименс Акциенгезелльшафт Method for enlarging burner size, and refractory burner arch changed as to size
RU2460944C2 (en) * 2008-04-01 2012-09-10 Сименс Акциенгезелльшафт Fire-resistant burner arches
RU2462664C2 (en) * 2008-04-01 2012-09-27 Сименс Акциенгезелльшафт Auxiliary combustion chamber in burner
RU2468298C2 (en) * 2008-04-01 2012-11-27 Сименс Акциенгезелльшафт Stage-by-stage fuel combustion in burner
RU2470229C2 (en) * 2008-04-01 2012-12-20 Сименс Акциенгезелльшафт Burner
CN101981378B (en) * 2008-04-01 2013-02-06 西门子公司 Passage in a burner
CN101983305B (en) * 2008-04-01 2013-02-06 西门子公司 Burner
US8561409B2 (en) 2008-04-01 2013-10-22 Siemens Aktiengesellschaft Quarls in a burner
CN101981380B (en) * 2008-04-01 2014-06-25 西门子公司 Pilot combustor in a burner
US8863524B2 (en) 2008-04-01 2014-10-21 Siemens Aktiengesellschaft Burner

Also Published As

Publication number Publication date
FR1150640A (en) 1958-01-16

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