GB623615A - Improvements in or relating to gas-turbine-engines - Google Patents
Improvements in or relating to gas-turbine-enginesInfo
- Publication number
- GB623615A GB623615A GB12268/47A GB1226847A GB623615A GB 623615 A GB623615 A GB 623615A GB 12268/47 A GB12268/47 A GB 12268/47A GB 1226847 A GB1226847 A GB 1226847A GB 623615 A GB623615 A GB 623615A
- Authority
- GB
- United Kingdom
- Prior art keywords
- members
- turbine
- holes
- bearing
- air
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
- F01D25/125—Cooling of bearings
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- 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
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- 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)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
623,615. Jet-propulsion gas turbine plant. MORLEY, F. W. W., and GARDINER, T. E. G. May 6, 1947, No. 12268. [Class 110(iii)] In a gas turbine plant for jet-propulsion, having the turbine and compressor rotors supported by three bearings, one at each end of the axial-flow compressor and the third on the down-stream side of the turbine rotor, the third bearing is carried in a housing supported in the turbine stationary structure, or in the exhaust assembly, by four radial members which have radially sliding engagement with the supporting structure. A stub shaft 21 is formed on the down-stream side of the turbine disc 11a and the outer member of the bearing 20 is carried by a ring 24 of T- shaped cross-section. The ring is secured to an annular member comprising a dished disc 22 and a hollow rim 23. The rim has four flanged ports to which are secured the flared inner ends 28 of members 27. The members 27, which lie obliquely in radial planes, pass through the exhaust assembly and are slidingly supported in it by sleeves 29. Two opposite members 27 form pipes by which cooling air is led to the hollow rim 23 and the other two contain pipes 36 for leading oil to nozzles 37 which direct the oil on to the bearing. Some air from the hollow rim 23 passes through holes 33 and between the turbine disc and a cover plate 34 and escapes into the exhaust stream. Other air passes up the members 27 around the oil pipes 36, part going through holes 39 into a cavity 40 and escaping to exhaust through holes 41 and 42 and part going through holes 38 into the space 17. Ports 39 occur also in the two members 27 which lead the air inwards.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB268648X | 1947-05-06 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB623615A true GB623615A (en) | 1949-05-19 |
Family
ID=10250437
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB12268/47A Expired GB623615A (en) | 1947-05-06 | 1947-05-06 | Improvements in or relating to gas-turbine-engines |
Country Status (2)
Country | Link |
---|---|
CH (1) | CH268648A (en) |
GB (1) | GB623615A (en) |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE945001C (en) * | 1951-09-27 | 1956-06-28 | Canadian Patents Dev | Gas turbine engine |
DE952668C (en) * | 1953-07-03 | 1956-11-22 | Armstrong Siddeley Motors Ltd | Exhaust cone for gas turbines |
DE1235072B (en) * | 1963-03-07 | 1967-02-23 | Daimler Benz Ag | Flexible bearing housing suspension on the outer wall of a gas turbine engine |
GB2118630A (en) * | 1982-04-19 | 1983-11-02 | United Technologies Corp | Structure for directing cooling air onto a turbine disc |
WO1999014464A1 (en) * | 1997-09-12 | 1999-03-25 | Bmw Rolls-Royce Gmbh | Turbofan aircraft engine |
EP1318275A2 (en) * | 2001-12-10 | 2003-06-11 | Nuovo Pignone Holding S.P.A. | Structure for separating the high and low pressure turboexpanders of a gas turbine |
EP1793091A1 (en) * | 2005-12-01 | 2007-06-06 | Siemens Aktiengesellschaft | Steam turbine with bearing struts |
DE102010001059A1 (en) * | 2010-01-20 | 2011-07-21 | Rolls-Royce Deutschland Ltd & Co KG, 15827 | Intermediate housing for a gas turbine engine |
EP2187019A4 (en) * | 2008-01-10 | 2015-02-25 | Mitsubishi Heavy Ind Ltd | Exhaust section structure of gas turbine and gas turbine |
US20150152786A1 (en) * | 2012-06-08 | 2015-06-04 | Siemens Aktiengesellschaft | Drain pipe arrangement and gas turbine engine comprising a drain pipe arrangement |
EP3358140A1 (en) * | 2017-02-06 | 2018-08-08 | United Technologies Corporation | Fitting for multiwall tube |
US10385710B2 (en) | 2017-02-06 | 2019-08-20 | United Technologies Corporation | Multiwall tube and fitting for bearing oil supply |
US10393303B2 (en) | 2017-02-06 | 2019-08-27 | United Technologies Corporation | Threaded fitting for tube |
US10465828B2 (en) | 2017-02-06 | 2019-11-05 | United Technologies Corporation | Tube fitting |
CN115680892A (en) * | 2022-08-29 | 2023-02-03 | 中国航发四川燃气涡轮研究院 | Air entraining structure for cooling remote measuring device of aircraft engine in high-temperature environment |
CN117569923A (en) * | 2024-01-12 | 2024-02-20 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB942842A (en) * | 1961-05-10 | 1963-11-27 | Rolls Royce | Gas turbine engine |
GB946597A (en) * | 1961-05-29 | 1964-01-15 | Rolls Royce | Fluid flow machine |
DE1238723B (en) * | 1963-03-07 | 1967-04-13 | Daimler Benz Ag | Arrangement of equipment lines on gas turbine engines |
US3312448A (en) * | 1965-03-01 | 1967-04-04 | Gen Electric | Seal arrangement for preventing leakage of lubricant in gas turbine engines |
-
1947
- 1947-05-06 GB GB12268/47A patent/GB623615A/en not_active Expired
-
1948
- 1948-05-04 CH CH268648D patent/CH268648A/en unknown
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE945001C (en) * | 1951-09-27 | 1956-06-28 | Canadian Patents Dev | Gas turbine engine |
DE952668C (en) * | 1953-07-03 | 1956-11-22 | Armstrong Siddeley Motors Ltd | Exhaust cone for gas turbines |
DE1235072B (en) * | 1963-03-07 | 1967-02-23 | Daimler Benz Ag | Flexible bearing housing suspension on the outer wall of a gas turbine engine |
GB2118630A (en) * | 1982-04-19 | 1983-11-02 | United Technologies Corp | Structure for directing cooling air onto a turbine disc |
WO1999014464A1 (en) * | 1997-09-12 | 1999-03-25 | Bmw Rolls-Royce Gmbh | Turbofan aircraft engine |
US6260352B1 (en) | 1997-09-12 | 2001-07-17 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofan aircraft engine |
EP1318275A2 (en) * | 2001-12-10 | 2003-06-11 | Nuovo Pignone Holding S.P.A. | Structure for separating the high and low pressure turboexpanders of a gas turbine |
EP1318275A3 (en) * | 2001-12-10 | 2004-09-08 | Nuovo Pignone Holding S.P.A. | Structure for separating the high and low pressure turboexpanders of a gas turbine |
US8550773B2 (en) * | 2005-12-01 | 2013-10-08 | Siemens Aktiengesellschaft | Steam turbine having bearing struts |
WO2007063088A1 (en) * | 2005-12-01 | 2007-06-07 | Siemens Aktiengesellschaft | Steam turbine having bearing struts |
JP2009517592A (en) * | 2005-12-01 | 2009-04-30 | シーメンス アクチエンゲゼルシヤフト | Steam turbine with bearing post |
US20100054927A1 (en) * | 2005-12-01 | 2010-03-04 | Henning Almstedt | Steam Turbine Having Bearing Struts |
CN101321929B (en) * | 2005-12-01 | 2011-01-26 | 西门子公司 | Steam turbine with bearing struts |
EP1793091A1 (en) * | 2005-12-01 | 2007-06-06 | Siemens Aktiengesellschaft | Steam turbine with bearing struts |
EP2187019A4 (en) * | 2008-01-10 | 2015-02-25 | Mitsubishi Heavy Ind Ltd | Exhaust section structure of gas turbine and gas turbine |
DE102010001059A1 (en) * | 2010-01-20 | 2011-07-21 | Rolls-Royce Deutschland Ltd & Co KG, 15827 | Intermediate housing for a gas turbine engine |
US8857193B2 (en) | 2010-01-20 | 2014-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Intermediate casing for a gas-turbine engine |
US20150152786A1 (en) * | 2012-06-08 | 2015-06-04 | Siemens Aktiengesellschaft | Drain pipe arrangement and gas turbine engine comprising a drain pipe arrangement |
US9932898B2 (en) * | 2012-06-08 | 2018-04-03 | Siemens Aktiengesellschaft | Drain pipe arrangement and gas turbine engine comprising a drain pipe arrangement |
EP3358140A1 (en) * | 2017-02-06 | 2018-08-08 | United Technologies Corporation | Fitting for multiwall tube |
US10385710B2 (en) | 2017-02-06 | 2019-08-20 | United Technologies Corporation | Multiwall tube and fitting for bearing oil supply |
US10393303B2 (en) | 2017-02-06 | 2019-08-27 | United Technologies Corporation | Threaded fitting for tube |
US10465828B2 (en) | 2017-02-06 | 2019-11-05 | United Technologies Corporation | Tube fitting |
US10830139B2 (en) | 2017-02-06 | 2020-11-10 | Raytheon Technologies Corporation | Fitting for multiwall tube |
CN115680892A (en) * | 2022-08-29 | 2023-02-03 | 中国航发四川燃气涡轮研究院 | Air entraining structure for cooling remote measuring device of aircraft engine in high-temperature environment |
CN115680892B (en) * | 2022-08-29 | 2024-05-17 | 中国航发四川燃气涡轮研究院 | Air entraining structure for cooling telemetry device of high-temperature environment of aeroengine |
CN117569923A (en) * | 2024-01-12 | 2024-02-20 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
CN117569923B (en) * | 2024-01-12 | 2024-04-05 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
Also Published As
Publication number | Publication date |
---|---|
CH268648A (en) | 1950-05-31 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB623615A (en) | Improvements in or relating to gas-turbine-engines | |
US2488875A (en) | Gas turbine engine | |
GB622181A (en) | Improvements relating to gas-turbine-engines | |
GB1281786A (en) | Turbine nozzles | |
GB804922A (en) | Improvements in or relating to axial-flow fluid machines for example compressors andturbines | |
GB618525A (en) | Improvements in or relating to gas-turbine engines | |
GB904138A (en) | Improvements in or relating to stator structures, for example for axial flow gas turbine engines | |
GB803137A (en) | Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines | |
GB645258A (en) | Improvements in or relating to turbines | |
GB730506A (en) | Improvements in or relating to gas turbine engines | |
GB622895A (en) | Improvements relating to axial flow compressors | |
GB709210A (en) | Improvements in gas turbine engines | |
GB736800A (en) | Improvements in or relating to stationary blade rings of axial flow turbines or compressors | |
GB885951A (en) | Arrangement for withdrawing cooling air from the compressor of a turbine engine | |
GB758108A (en) | Improvements in turbine nozzles | |
GB749577A (en) | Improvements in or relating to blade ring assemblies for axial flow compressors or turbines | |
GB911160A (en) | Improvements in or relating to engines having gas compressors | |
GB787666A (en) | Improvements in blades for gas turbine engines | |
GB585331A (en) | Improvements in or relating to internal-combustion turbines | |
GB629770A (en) | Improvements in or relating to sealing rings for turbines | |
GB586569A (en) | Improvements in and relating to internal combustion turbine plant | |
GB802906A (en) | Improvements in or relating to combustion turbine engines comprising axial flow compressors | |
GB744548A (en) | Improvements in or relating to gas turbines | |
GB741549A (en) | Improvements in or relating to the stators of multi-stage axial flow compressors or turbines | |
GB610572A (en) | Twin expansion turbine for production of low temperatures |