GB798865A - Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines - Google Patents

Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines

Info

Publication number
GB798865A
GB798865A GB36737/55A GB3673755A GB798865A GB 798865 A GB798865 A GB 798865A GB 36737/55 A GB36737/55 A GB 36737/55A GB 3673755 A GB3673755 A GB 3673755A GB 798865 A GB798865 A GB 798865A
Authority
GB
United Kingdom
Prior art keywords
air
scoop
flame tube
openings
disposed
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
GB36737/55A
Inventor
Morris Amos Stokes
Robert William Oliver Papworth
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors Ltd
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 Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Priority to GB36737/55A priority Critical patent/GB798865A/en
Priority to US628086A priority patent/US2841958A/en
Publication of GB798865A publication Critical patent/GB798865A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60Support structures; Attaching or mounting means
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

798,865. Generating combustion products under pressure. ARMSTRONG SIDDELEY MOTORS, Ltd. Dec. 6, 1956 [Dec. 22, 1955], No. 36737/55. Class 51 (1). In a combustion system for an engine, of the kind comprising a flame tube disposed within an outer air casing, a ring of openings or ports is disposed in the flame tube for admission of air to the combustion space and an annular, forwardly-facing curved scoop is disposed in the air space between the flame tube and the outer casing to guide air to the admission ports. The space within the scoop is divided circumferentially by a number of axially-directed, radiallyextending splitter struts, each pair of struts defining with the adjacent portion of the scoop a flow passage terminating in an admission port. The engine may be an axial-flow gas turbine engine (particularly of the jet-propulsion type) or a ram jet engine. In the gas turbine engine combustion equipment shown in Fig. 2, an annular flame tube built up of sectional parts 17, 18, 19, 20, 21, 22, 23, 24 is disposed between outer and inner air casing walls 15, 16, the flame tube sections being spaced apart by means of corrugated spacers 25. Air admission ports 28 are provided in the flame tube section 19 and similar ports are provided in the corresponding section 20. The downstream portion of the section 19 is shaped to form a forwardly-facing scoop 31 and struts 33 are disposed beneath the scoop between the upstream and downstream portions of the section 19, the air admission ports 28 being provided between adjacent struts 33 and the two parts of the flame tube section 19. The struts are hollow, being provided adjacent the inlet edge with openings 46 and in the floor portion 36 with openings 47 for flow of cooling air therethrough. The struts are each supported by means of a stud 34 secured to the air casing'15 which engages slidingly in a boss secured within the strut. A baffle 49 is disposed within the air space downstream of the scoop 31 so that cooling air flowing past the scoop does not have its velocity reduced. The scoop 32 associated with the flame tube inner wall section 20 is similarly arranged. In Fig. 6 two axially-spaced rows of air admission openings 62, 63 are provided in the flame tube outer wall section 60 and two air scoops 64, 65 are disposed between the flame tube section and the outer air casing wall, the inlet to the scoop 64 which leads to the openings 62 being upstream of the inlet to the scoop 65 which leads to the openings 63. The inner wall of the passages leading to the openings 63 is afforded by a fairing 66. In a similar embodiment in which the two rows of air admission openings are spaced closer together, the inlets to the two scoops are at the same axial location and the fairing 66 is not necessary. The invention is applied in a similar manner to a tube type of combustion equipment.
GB36737/55A 1955-12-22 1955-12-22 Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines Expired GB798865A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB36737/55A GB798865A (en) 1955-12-22 1955-12-22 Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines
US628086A US2841958A (en) 1955-12-22 1956-12-13 Combustion system of the kind comprising an outer air casing containing a flame compartment for use in gas turbine engines and ram jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB36737/55A GB798865A (en) 1955-12-22 1955-12-22 Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines

Publications (1)

Publication Number Publication Date
GB798865A true GB798865A (en) 1958-07-30

Family

ID=10390795

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36737/55A Expired GB798865A (en) 1955-12-22 1955-12-22 Improvements in and relating to combustion systems for axial-flow gas turbine engines and ram jet engines

Country Status (2)

Country Link
US (1) US2841958A (en)
GB (1) GB798865A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1148817B (en) * 1959-06-23 1963-05-16 Rolls Royce Twin-flow gas turbine jet engine
US6241468B1 (en) 1998-10-06 2001-06-05 Rolls-Royce Plc Coolant passages for gas turbine components

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3581492A (en) * 1969-07-08 1971-06-01 Nasa Gas turbine combustor
GB2135440B (en) * 1983-02-19 1986-06-25 Rolls Royce Mounting combustion chambers
US4815276A (en) * 1987-09-10 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Borescope plug
KR101766449B1 (en) 2016-06-16 2017-08-08 두산중공업 주식회사 Air flow guide cap and combustion duct having the same
KR101863774B1 (en) * 2017-09-06 2018-06-01 두산중공업 주식회사 Scoop arrangement for enhancing cooling performance of transition piece and a gas turbine combustor using the same
CN112916734A (en) * 2021-01-25 2021-06-08 中国航发贵州黎阳航空动力有限公司 Integral forming die and forming method for inner ring of flame tube of gas turbine
CN116428615B (en) * 2023-05-23 2024-05-10 浙江大学 Circumferential circulation combustor between turbine stages

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1148817B (en) * 1959-06-23 1963-05-16 Rolls Royce Twin-flow gas turbine jet engine
US6241468B1 (en) 1998-10-06 2001-06-05 Rolls-Royce Plc Coolant passages for gas turbine components

Also Published As

Publication number Publication date
US2841958A (en) 1958-07-08

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