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 enginesInfo
- 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
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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
-
- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
- F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
-
- 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
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.
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)
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)
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 |
-
1955
- 1955-12-22 GB GB36737/55A patent/GB798865A/en not_active Expired
-
1956
- 1956-12-13 US US628086A patent/US2841958A/en not_active Expired - Lifetime
Cited By (2)
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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