GB1060095A - Improvements relating to the flow of a cooling fluid - Google Patents
Improvements relating to the flow of a cooling fluidInfo
- Publication number
- GB1060095A GB1060095A GB2002264A GB2002264A GB1060095A GB 1060095 A GB1060095 A GB 1060095A GB 2002264 A GB2002264 A GB 2002264A GB 2002264 A GB2002264 A GB 2002264A GB 1060095 A GB1060095 A GB 1060095A
- Authority
- GB
- United Kingdom
- Prior art keywords
- adjacent
- corrugated
- cooling air
- annular
- sections
- 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
- F23R3/02—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
- F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1, 060, 095. Gas turbine engine combustion chambers. ROLLS-ROYCE Ltd. May 6, 1965 [May 13, 1964], No.20022/64. Heading F1L A gas turbine engine combustion chamber comprises a flame tube formed of a series of tubular sections which overlap at their adjacent ends to provide annular passages through which cooling air may flow so as to provide a film of cooling air over the inner surface of the adjacent downstream section, a corrugated annular member being disposed in the annular passage between adjacent sections, the corrugated member having an inclined end face which extends to the wall of the downstream section which reduces the tendency for the film of cooling air to break away from the surface. In Fig. 2 portions of the adjacent flame tube sections are indicated at 14, 15 and the annular gap therebetween at 26, a corrugated spacer member 30 being disposed in the gap, the downstream end of the corrugated spacer being inclined with respect to the inner surface of the adjacent section as indicated at 33.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2002264A GB1060095A (en) | 1964-05-13 | 1964-05-13 | Improvements relating to the flow of a cooling fluid |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2002264A GB1060095A (en) | 1964-05-13 | 1964-05-13 | Improvements relating to the flow of a cooling fluid |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1060095A true GB1060095A (en) | 1967-02-22 |
Family
ID=10139071
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2002264A Expired GB1060095A (en) | 1964-05-13 | 1964-05-13 | Improvements relating to the flow of a cooling fluid |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1060095A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1989006308A1 (en) * | 1987-12-28 | 1989-07-13 | Sundstrand Corporation | Annular combustor with tangential cooling air injection |
US5327727A (en) * | 1993-04-05 | 1994-07-12 | General Electric Company | Micro-grooved heat transfer combustor wall |
US5337568A (en) * | 1993-04-05 | 1994-08-16 | General Electric Company | Micro-grooved heat transfer wall |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
US5653110A (en) * | 1991-07-22 | 1997-08-05 | General Electric Company | Film cooling of jet engine components |
US5680767A (en) * | 1995-09-11 | 1997-10-28 | General Electric Company | Regenerative combustor cooling in a gas turbine engine |
CN106705075A (en) * | 2016-12-12 | 2017-05-24 | 深圳智慧能源技术有限公司 | Torch with forced-cooling air film |
-
1964
- 1964-05-13 GB GB2002264A patent/GB1060095A/en not_active Expired
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1989006308A1 (en) * | 1987-12-28 | 1989-07-13 | Sundstrand Corporation | Annular combustor with tangential cooling air injection |
US4928479A (en) * | 1987-12-28 | 1990-05-29 | Sundstrand Corporation | Annular combustor with tangential cooling air injection |
USRE34962E (en) * | 1987-12-28 | 1995-06-13 | Sundstrand Corporation | Annular combustor with tangential cooling air injection |
US5653110A (en) * | 1991-07-22 | 1997-08-05 | General Electric Company | Film cooling of jet engine components |
US5327727A (en) * | 1993-04-05 | 1994-07-12 | General Electric Company | Micro-grooved heat transfer combustor wall |
US5337568A (en) * | 1993-04-05 | 1994-08-16 | General Electric Company | Micro-grooved heat transfer wall |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
US5680767A (en) * | 1995-09-11 | 1997-10-28 | General Electric Company | Regenerative combustor cooling in a gas turbine engine |
CN106705075A (en) * | 2016-12-12 | 2017-05-24 | 深圳智慧能源技术有限公司 | Torch with forced-cooling air film |
CN106705075B (en) * | 2016-12-12 | 2023-12-12 | 深圳智慧能源技术有限公司 | Forced air film cooling torch |
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