GB700688A - Improvements in or relating to gas-turbine engines - Google Patents
Improvements in or relating to gas-turbine enginesInfo
- Publication number
- GB700688A GB700688A GB30153/50A GB3015350A GB700688A GB 700688 A GB700688 A GB 700688A GB 30153/50 A GB30153/50 A GB 30153/50A GB 3015350 A GB3015350 A GB 3015350A GB 700688 A GB700688 A GB 700688A
- Authority
- GB
- United Kingdom
- Prior art keywords
- struts
- chambers
- diffuser
- annular
- downstream
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
700,688. Gas turbine plant; axial flow compressors. ROLLS-ROYCE, Ltd. Nov. 30, 1951 [Dec. 8, 1950], No. 30153/50. Classes 110 (1) and 110 (3) In a gas turbine engine employing an axial flow compressor connected to the combustion chamber or chambers by an annular diffuser having inner and outer walls 15, 16 connected by axially extending hollow radial struts 17, the struts are provided with air inlet apertures 25 and an outlet connection 32 is provided whereby air may be tapped from the interior of the struts. The struts communicate at their downstream ends with an annular manifold 29 formed by a part 28 bolted to a flange 26 and in sealing engagement with a flange 27, both flanges being formed on the inner wall of the diffuser. The diffuser is secured to an annular combustion chamber provided with an annular flame tube or with a series of tubular flame tubes 23 arranged between, and axially overlapped by, the struts 17. The uostream ends of the flame tubes may be supported as described in Specification 686,383, [Group XII]. Alternatively a number of separate tubular combustion chambers may be provided, the downstream end of each strut dividing to provide a side wall of each of two adjacent branch connections to adjacent chambers. The interior of a strut may be divided into two or more chambers and those through which air is not tapped off may be used as breather passages for the interior of the engine, or to permit passage of auxiliary drive shafts. In the modification shown in Fig. 4, the manifold is cast in one with the diffuser. It is divided into downstream and upstream portions 52, 51 by a circumferential rib 53a and these portions may be further subdivided by axial ribs 58, Fig. 7. The hollow struts are divided into chambers 48, 49 by partitions 50 and the air inlet apertures 55 are in some struts on the downstream side, and in others on the upstream side of the partitions. Certain struts have tapping outlets 57. Air inlet anertures may be nrovided in the leading edge of the struts and outleak apertures may be provided on the trailing edges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB30153/50A GB700688A (en) | 1950-12-08 | 1950-12-08 | Improvements in or relating to gas-turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB30153/50A GB700688A (en) | 1950-12-08 | 1950-12-08 | Improvements in or relating to gas-turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB700688A true GB700688A (en) | 1953-12-09 |
Family
ID=10303157
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB30153/50A Expired GB700688A (en) | 1950-12-08 | 1950-12-08 | Improvements in or relating to gas-turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB700688A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1184560B (en) * | 1960-03-14 | 1964-12-31 | Rolls Royce | Heat exchangers, in particular for de-icing inlet struts for gas turbine engines |
| FR2527268A1 (en) * | 1982-05-20 | 1983-11-25 | United Technologies Corp | PREDIFFUSER FOR A GAS TURBINE ENGINE |
| DE3333437A1 (en) * | 1983-09-16 | 1985-04-11 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Device for controlling the compressor of gas turbine engines |
| EP0296058A1 (en) * | 1987-06-18 | 1988-12-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Casing of a turbine combustion chamber, comprising air outlet ports |
| FR2616890A1 (en) * | 1987-06-18 | 1988-12-23 | Snecma | Annular combustion chamber, with casing in the form of box sections, for turbo machines |
| GB2251031A (en) * | 1990-12-19 | 1992-06-24 | Rolls Royce Plc | Cooling air pick up for gas turbine engine |
| WO1995004225A1 (en) * | 1993-08-02 | 1995-02-09 | Siemens Aktiengesellschaft | Process and device for tapping a partial stream from a stream of compressed gas |
| WO2010130959A1 (en) * | 2009-05-14 | 2010-11-18 | Snecma | Diffuser for a turbine engine |
| WO2015155452A1 (en) | 2014-04-09 | 2015-10-15 | Turbomeca | Aircraft engine comprising azimuth setting of the diffuser with respect to the combustion chamber |
-
1950
- 1950-12-08 GB GB30153/50A patent/GB700688A/en not_active Expired
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1184560B (en) * | 1960-03-14 | 1964-12-31 | Rolls Royce | Heat exchangers, in particular for de-icing inlet struts for gas turbine engines |
| FR2527268A1 (en) * | 1982-05-20 | 1983-11-25 | United Technologies Corp | PREDIFFUSER FOR A GAS TURBINE ENGINE |
| GB2120325A (en) * | 1982-05-20 | 1983-11-30 | United Technologies Corp | Prediffuser for a gas turbine engine |
| DE3333437A1 (en) * | 1983-09-16 | 1985-04-11 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Device for controlling the compressor of gas turbine engines |
| EP0296058A1 (en) * | 1987-06-18 | 1988-12-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Casing of a turbine combustion chamber, comprising air outlet ports |
| FR2616889A1 (en) * | 1987-06-18 | 1988-12-23 | Snecma | TURBOREACTOR COMBUSTION CHAMBER CASING COMPRISING AIR LEAK ORIFICES |
| FR2616890A1 (en) * | 1987-06-18 | 1988-12-23 | Snecma | Annular combustion chamber, with casing in the form of box sections, for turbo machines |
| GB2251031A (en) * | 1990-12-19 | 1992-06-24 | Rolls Royce Plc | Cooling air pick up for gas turbine engine |
| GB2251031B (en) * | 1990-12-19 | 1995-01-18 | Rolls Royce Plc | Cooling air pick up |
| WO1995004225A1 (en) * | 1993-08-02 | 1995-02-09 | Siemens Aktiengesellschaft | Process and device for tapping a partial stream from a stream of compressed gas |
| WO2010130959A1 (en) * | 2009-05-14 | 2010-11-18 | Snecma | Diffuser for a turbine engine |
| FR2945589A1 (en) * | 2009-05-14 | 2010-11-19 | Snecma | DIFFUSER. |
| WO2015155452A1 (en) | 2014-04-09 | 2015-10-15 | Turbomeca | Aircraft engine comprising azimuth setting of the diffuser with respect to the combustion chamber |
| FR3019879A1 (en) * | 2014-04-09 | 2015-10-16 | Turbomeca | AIRCRAFT ENGINE COMPRISING AN AZIMUTAL SHIFT OF THE DIFFUSER, IN RELATION TO THE COMBUSTION CHAMBER |
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