GB818634A - Improvements in or relating to combustion chambers for gas turbines - Google Patents
Improvements in or relating to combustion chambers for gas turbinesInfo
- Publication number
- GB818634A GB818634A GB2769155A GB2769155A GB818634A GB 818634 A GB818634 A GB 818634A GB 2769155 A GB2769155 A GB 2769155A GB 2769155 A GB2769155 A GB 2769155A GB 818634 A GB818634 A GB 818634A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wall
- combustion zone
- throat
- divergent
- 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
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
818,634. Generating combustion products under pressure. BIRMINGHAM SMALL ARMS CO. Ltd. Sept. 5, 1956 [Sept. 29, 1955], No. 27691/55. Class 51 (1). A flame tube for combustion equipment of a gas turbine engine comprises a primary combustion zone which diverges from the fuel inlet at one end and converges sharply to a throat at the other end and a secondary combustion zone diverging from the throat. Apertures are provided in the divergent wall of the primary combustion zone for admission of primary air, and apertures are also provided in the divergent wall of the secondary combustion zone for admission of secondary air. The flame tube in Fig. 1 comprises a primary combustion zone formed by a divergent wall 4 and a convergent wall 5 connected by a curved portion 6, the wall 5 being followed by a curved portion 8 and divergent wall 7 which define a throat 9 and a secondary combustion zone respectively. The wall 7 is followed by a cylindrical wall portion 10 which defines a mixing zone and terminates in a combustion gas outlet 11. Primary air inlet openings 12, 13 are provided in the divergent wall 4, secondary air inlet openings 15 are provided in the divergent wall 7 and mixing or tertiary air inlet openings 16 are provided in the cylindrical wall 10. A tubular portion 2 is provided at the upstream end of the divergent wall 4 and is adapted to receive a fuel injector 3. An air-swirling ring 14 may be disposed around the air inlet openings 13. The flame tube is disposed within an outer easing 17 through which air may flow from an inlet either at the upstream end, at the downstream end 19, or at the middle 18. In a second embodiment, the flame tube wall diverges uniformly from the throat to the outlet, secondary and dilution air inlet openings being provided at appropriate points. In further embodiments, similar to Fig. 1, the wall 10 of the mixing portion either gradually diverges or gradually converges from the sharply divergent wall 7 of the secondary combustion zone to the outlet of the flame tube. The primary combustion zone in Fig. 6 is essentially spherical and terminates in a throat 44 while that in Fig. 7 is pear-shaped terminating in a throat 53. Alternative forms for the secondary combustion and mixing zones are indicated in Figs. 6 and 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2769155A GB818634A (en) | 1955-09-29 | 1955-09-29 | Improvements in or relating to combustion chambers for gas turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2769155A GB818634A (en) | 1955-09-29 | 1955-09-29 | Improvements in or relating to combustion chambers for gas turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB818634A true GB818634A (en) | 1959-08-19 |
Family
ID=10263735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2769155A Expired GB818634A (en) | 1955-09-29 | 1955-09-29 | Improvements in or relating to combustion chambers for gas turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB818634A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2406075A1 (en) * | 1977-10-11 | 1979-05-11 | Snecma | COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS |
| EP0845639A1 (en) * | 1996-11-29 | 1998-06-03 | Abb Research Ltd. | Combustor |
| EP1522792A1 (en) * | 2003-10-09 | 2005-04-13 | United Technologies Corporation | Combustor |
| GB2441342A (en) * | 2006-09-01 | 2008-03-05 | Rolls Royce Plc | Wall Elements for Gas Turbine Engine Components |
| US7954325B2 (en) | 2005-12-06 | 2011-06-07 | United Technologies Corporation | Gas turbine combustor |
| US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
| US9068748B2 (en) | 2011-01-24 | 2015-06-30 | United Technologies Corporation | Axial stage combustor for gas turbine engines |
| US20160223196A1 (en) * | 2015-02-02 | 2016-08-04 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Crude Oil Spray Combustor |
| US9958162B2 (en) | 2011-01-24 | 2018-05-01 | United Technologies Corporation | Combustor assembly for a turbine engine |
| WO2018057072A3 (en) * | 2016-06-22 | 2018-07-26 | General Electric Company | Combustor assembly for a gas turbine engine |
| US11022313B2 (en) | 2016-06-22 | 2021-06-01 | General Electric Company | Combustor assembly for a turbine engine |
| US11181269B2 (en) | 2018-11-15 | 2021-11-23 | General Electric Company | Involute trapped vortex combustor assembly |
| US20230250961A1 (en) * | 2022-02-07 | 2023-08-10 | General Electric Company | Combustor with a variable primary zone combustion chamber |
-
1955
- 1955-09-29 GB GB2769155A patent/GB818634A/en not_active Expired
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2406075A1 (en) * | 1977-10-11 | 1979-05-11 | Snecma | COMBUSTION APPARATUS AND ITS EMBODIMENT PROCESS |
| EP0845639A1 (en) * | 1996-11-29 | 1998-06-03 | Abb Research Ltd. | Combustor |
| EP1522792A1 (en) * | 2003-10-09 | 2005-04-13 | United Technologies Corporation | Combustor |
| US7093441B2 (en) | 2003-10-09 | 2006-08-22 | United Technologies Corporation | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
| US7954325B2 (en) | 2005-12-06 | 2011-06-07 | United Technologies Corporation | Gas turbine combustor |
| GB2441342A (en) * | 2006-09-01 | 2008-03-05 | Rolls Royce Plc | Wall Elements for Gas Turbine Engine Components |
| GB2441342B (en) * | 2006-09-01 | 2009-03-18 | Rolls Royce Plc | Wall elements with apertures for gas turbine engine components |
| US9068748B2 (en) | 2011-01-24 | 2015-06-30 | United Technologies Corporation | Axial stage combustor for gas turbine engines |
| US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
| US9958162B2 (en) | 2011-01-24 | 2018-05-01 | United Technologies Corporation | Combustor assembly for a turbine engine |
| US20160223196A1 (en) * | 2015-02-02 | 2016-08-04 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Crude Oil Spray Combustor |
| WO2018057072A3 (en) * | 2016-06-22 | 2018-07-26 | General Electric Company | Combustor assembly for a gas turbine engine |
| US10197279B2 (en) | 2016-06-22 | 2019-02-05 | General Electric Company | Combustor assembly for a turbine engine |
| US11022313B2 (en) | 2016-06-22 | 2021-06-01 | General Electric Company | Combustor assembly for a turbine engine |
| US11181269B2 (en) | 2018-11-15 | 2021-11-23 | General Electric Company | Involute trapped vortex combustor assembly |
| US20230250961A1 (en) * | 2022-02-07 | 2023-08-10 | General Electric Company | Combustor with a variable primary zone combustion chamber |
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