GB610113A - Improvements in or relating to gas-turbine engines - Google Patents
Improvements in or relating to gas-turbine enginesInfo
- Publication number
- GB610113A GB610113A GB9203/46A GB920346A GB610113A GB 610113 A GB610113 A GB 610113A GB 9203/46 A GB9203/46 A GB 9203/46A GB 920346 A GB920346 A GB 920346A GB 610113 A GB610113 A GB 610113A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- turbine
- compressor
- combustion chambers
- casing
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- 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)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
610,113. Jet propulsion plant. LOMBARD, A. A. March 25, 1946, No. 9203. [Class 110 (iii)] The invention relates to an internal-combustion gas turbine plant of the kind in which a compressor is driven by a coaxial axial flow turbine by a driving shaft extending between the turbine and compressor, the air from the compressor passing to a number of combustion chambers which are arranged in a ring around the driving shaft and deliver combustion products to an annular nozzle guide vane assembly and further in which there is provided an intermediate casing lying within the ring of combustion chambers between the compressor and turbine. The invention consists in the combination, in a turbine plant of the kind described, of a number of nozzle boxes adapted to convey combustion products from the combustion chambers to the nozzle guide vane assembly and a structure forming a chamber to accommodate the nozzle boxes, which structure includes a ring formed with apertures to support the outlet ends of the combustion chambers and is connected to the outer turbine structure and the intermediate casing to transmit structural loads therebetween. The turbine rotor 10, 11, Fig. 2, is supported from the compressor casing through a bearing 13 carried by a structure 14 extending from an intermediate casing 15 which is bolted to the compressor casing. The exhaust duct assembly 8, the turbine shroud ring 17 and the outer ring shroud 19 of the guide vane assembly are bolted together and attached by a conical ring 25 to an apertured ring 26 by which they are supported from the intermediate casing 15. The apertured ring 26 supports the ends of the combustion chambers 7 and the inlet ends of the nozzle boxes 33. The combustion chambers 7, Fig. 3, carry at their ends strengthening rings 7a which slide on the inner surfaces of a bush 31 inserted in the apertures of the ring 26. The nozzle boxes 33 are of fabricated sheet metal and are welded as at 34 to a ring 35. The ring 35 and bush 31 are attached to the apertured ring 26 by bolts 36. The exit ends of the nozzle boxes are supported between the casing 23 and the ring 37 disposed between the outer shroud ring 19 and the conical ring 25. Bolted to the inner diameter of the apertured ring 26 is a tubular member 23 which carries at its rearward end the inner guide vane shroud ring 20 and seal 20a. The guide vanes 21 have radial clearance in rings 19 and 20 so that loads on these rings are not imparted to the blades. A sheet metal collector ring 40 is bolted to the nozzle box casing by studs 27 and 24 to form a cooling air space to which cooling air is taken from the interior of the member 23 by pipes (not shown). According to the Provisional Specification the members 25, 26 are castings, but may be made of sheet metal with flanges welded on.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE487120D BE487120A (en) | 1946-03-25 | ||
GB9203/46A GB610113A (en) | 1946-03-25 | 1946-03-25 | Improvements in or relating to gas-turbine engines |
US733912A US2494821A (en) | 1946-03-25 | 1947-03-11 | Means for supporting the nozzles of the combustion chambers of internal-combustion turbines |
FR943932D FR943932A (en) | 1946-03-25 | 1947-03-24 | Improvements to internal combustion turbines |
CH258674D CH258674A (en) | 1946-03-25 | 1948-08-18 | Combustion turbine unit. |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9203/46A GB610113A (en) | 1946-03-25 | 1946-03-25 | Improvements in or relating to gas-turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB610113A true GB610113A (en) | 1948-10-12 |
Family
ID=9867397
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9203/46A Expired GB610113A (en) | 1946-03-25 | 1946-03-25 | Improvements in or relating to gas-turbine engines |
Country Status (5)
Country | Link |
---|---|
US (1) | US2494821A (en) |
BE (1) | BE487120A (en) |
CH (1) | CH258674A (en) |
FR (1) | FR943932A (en) |
GB (1) | GB610113A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2442300A (en) * | 2006-09-27 | 2008-04-02 | Rolls Royce Plc | Sheet material gas turbine engine casing components |
US10465642B2 (en) | 2017-03-27 | 2019-11-05 | Kohler Co. | Carburetor drain |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2711074A (en) * | 1944-06-22 | 1955-06-21 | Gen Electric | Aft frame and rotor structure for combustion gas turbine |
FR963256A (en) * | 1947-03-14 | 1950-07-05 | ||
US2789787A (en) * | 1949-10-22 | 1957-04-23 | Svenska Turbinfab Ab | Guide blade device for steam or gas turbines |
US2608057A (en) * | 1949-12-24 | 1952-08-26 | A V Roe Canada Ltd | Gas turbine nozzle box |
US2763462A (en) * | 1950-01-11 | 1956-09-18 | Gen Motors Corp | Turbine casing construction |
US2609176A (en) * | 1950-01-21 | 1952-09-02 | A V Roe Canada Ltd | Turbine nozzle guide vane construction |
US2654566A (en) * | 1950-02-11 | 1953-10-06 | A V Roe Canada Ltd | Turbine nozzle guide vane construction |
US2747367A (en) * | 1950-03-21 | 1956-05-29 | United Aircraft Corp | Gas turbine power plant supporting structure |
US2699040A (en) * | 1950-05-23 | 1955-01-11 | Gen Motors Corp | Detachable combustion chamber for gas turbines |
US2780174A (en) * | 1951-03-19 | 1957-02-05 | Solar Aircraft Co | Pump and power plant assembly |
US2702454A (en) * | 1951-06-07 | 1955-02-22 | United Aircraft Corp | Transition piece providing a connection between the combustion chambers and the turbine nozzle in gas turbine power plants |
US2848191A (en) * | 1951-11-03 | 1958-08-19 | A V Roe Canada Ltd | Nozzle box |
US2839894A (en) * | 1952-12-31 | 1958-06-24 | Gen Motors Corp | Supporting arrangement for a gas turbine combustion chamber |
US2825285A (en) * | 1953-12-28 | 1958-03-04 | Belton A Copp | Centrifugal pump with discharge manifold |
BE570533A (en) * | 1957-08-22 | |||
DE1218800B (en) * | 1961-04-25 | 1966-06-08 | M A N Turbo Ges Mit Beschraenk | Gas turbine, in particular small gas turbine |
US4573315A (en) * | 1984-05-15 | 1986-03-04 | A/S Kongsberg Vapenfabrikk | Low pressure loss, convectively gas-cooled inlet manifold for high temperature radial turbine |
US6116013A (en) * | 1998-01-02 | 2000-09-12 | Siemens Westinghouse Power Corporation | Bolted gas turbine combustor transition coupling |
DE102010001059A1 (en) * | 2010-01-20 | 2011-07-21 | Rolls-Royce Deutschland Ltd & Co KG, 15827 | Intermediate housing for a gas turbine engine |
US9021783B2 (en) * | 2012-10-12 | 2015-05-05 | United Technologies Corporation | Pulse detonation engine having a scroll ejector attenuator |
US9470422B2 (en) | 2013-10-22 | 2016-10-18 | Siemens Energy, Inc. | Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier |
US9810434B2 (en) * | 2016-01-21 | 2017-11-07 | Siemens Energy, Inc. | Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine |
CN113154456B (en) * | 2021-04-15 | 2022-06-21 | 中国航发湖南动力机械研究所 | Head structure of casing of backflow combustion chamber, manufacturing method of head structure and engine combustion chamber |
CN115288804B (en) * | 2022-10-10 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Bird skeleton bionic force-bearing structure and design method thereof |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2432359A (en) * | 1947-12-09 | Internal-combustion turbine power | ||
GB588082A (en) * | 1941-08-25 | 1947-05-14 | Power Jets Ltd | Improvements relating to engines |
GB579331A (en) * | 1943-07-13 | 1946-07-31 | Francis Robert Bell | Improvements in combustion chambers for power-gas-generators, internal-combustion turbines and the like |
-
0
- BE BE487120D patent/BE487120A/xx unknown
-
1946
- 1946-03-25 GB GB9203/46A patent/GB610113A/en not_active Expired
-
1947
- 1947-03-11 US US733912A patent/US2494821A/en not_active Expired - Lifetime
- 1947-03-24 FR FR943932D patent/FR943932A/en not_active Expired
-
1948
- 1948-08-18 CH CH258674D patent/CH258674A/en unknown
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2442300A (en) * | 2006-09-27 | 2008-04-02 | Rolls Royce Plc | Sheet material gas turbine engine casing components |
GB2442300B (en) * | 2006-09-27 | 2009-01-28 | Rolls Royce Plc | Casing for a gas turbine engine |
US8057170B2 (en) | 2006-09-27 | 2011-11-15 | Rolls-Royce Plc | Intermediate casing for a gas turbine engine |
US10465642B2 (en) | 2017-03-27 | 2019-11-05 | Kohler Co. | Carburetor drain |
Also Published As
Publication number | Publication date |
---|---|
US2494821A (en) | 1950-01-17 |
BE487120A (en) | |
CH258674A (en) | 1948-12-15 |
FR943932A (en) | 1949-03-22 |
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