GB1316452A - Gas turbine engine - Google Patents
Gas turbine engineInfo
- Publication number
- GB1316452A GB1316452A GB3917370A GB1316452DA GB1316452A GB 1316452 A GB1316452 A GB 1316452A GB 3917370 A GB3917370 A GB 3917370A GB 1316452D A GB1316452D A GB 1316452DA GB 1316452 A GB1316452 A GB 1316452A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- rotor
- thermal expansion
- compressor
- engine
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1316452 Gas turbine engines DEFENCE SECRETARY OF STATE FOR 5 Aug 1971 [14 Aug 1970] 39173/70 Heading F1G A gas turbine engine comprises a rotor member, a shaft to which the rotor member is connected and which is supported in bearings which allow freedom for axial thermal-expansion of the shaft, the rotor member being spaced from a sealing member supported in static structure at a first radial plane of the engine by an axial sealing clearance, and the shaft being mounted on a member which is located in static structure at a second radial plane of the engine, the member being made of a material having a lower coefficient of thermal expansion than the shaft. In the by-pass gas turbine engine shown, the H. P. compressor rotors 7 are connected to the rotor of the H. P. turbine 13 by a shaft 14 supported by roller bearings 15, 16 which permit axial displacement due to thermal expansion. Endwise location of the shaft 14 is effected by a tubular member 20 which is attached to the shaft by a coupling 23 at a position between the rotors 7 and the rotor 13 and is located at its upstream end by a ball bearing 21. The member 20 is of a material having a lower co-efficient of thermal expansion than that of the shaft 14, whereby axial movement of the turbine rotor 13 relative to adjacent parts of the casing is reduced, so that a closer clearance between sealing members 17, 19 can be maintained. For the purpose of maintaining the temperature, and therefore the thermal expansion, of the member 20 at an accurately known value, air at a known temperature is bled from the compressor and supplied to the space 31 between the member 20 and a surrounding tube 32. Similarly, the portion of the engine casing surrounding the combustion chamber 11 may be of double-walled construction 40, 41 to provide an annular space 44 supplied with air at known temperature bled from the compressor. This air is exhausted via holes 45, 46 into the by-pass passage 5 or may instead be used for cooling hot parts of the turbine. The outer wall 40 is of the same low expansion material as the member 20, while the inner wall 41 is anchored at its downstream end and supports the stator of the H.P. compressor 6 through a sliding joint 43. To provide sealing where the burners 10 pass through the walls 40, 41 despite relative thermal expansion between the walls a sleeve 60 is screwed into a threaded aperture in the wall 41 and a cup 61 is dispersed between a shoulder 62 on the sleeve and the wall 41. The cup can slide axially relative to the sleeve and radially relative to the outer casing.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB3917370 | 1970-08-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1316452A true GB1316452A (en) | 1973-05-09 |
Family
ID=10408082
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3917370A Expired GB1316452A (en) | 1970-08-14 | 1970-08-14 | Gas turbine engine |
Country Status (5)
Country | Link |
---|---|
US (1) | US3709637A (en) |
JP (1) | JPS5217180B1 (en) |
DE (1) | DE2140337C3 (en) |
FR (1) | FR2102268B1 (en) |
GB (1) | GB1316452A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170058675A1 (en) * | 2015-08-31 | 2017-03-02 | Rolls-Royce Corporation | Low diameter turbine rotor clamping arrangement |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1443431A (en) * | 1972-12-16 | 1976-07-21 | Rolls Royce | Seal between relatively moving components of a fluid flow machine |
DE3315914A1 (en) * | 1983-05-02 | 1984-11-08 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | GAS TURBINE ENGINE WITH DEVICES FOR VANIZING GAPS |
US5165850A (en) * | 1991-07-15 | 1992-11-24 | General Electric Company | Compressor discharge flowpath |
US6053697A (en) * | 1998-06-26 | 2000-04-25 | General Electric Company | Trilobe mounting with anti-rotation apparatus for an air duct in a gas turbine rotor |
US6910858B2 (en) * | 2002-12-26 | 2005-06-28 | United Technologies Corporation | Seal |
US8967977B2 (en) * | 2010-08-30 | 2015-03-03 | United Technologies Corporation | Locked spacer for a gas turbine engine shaft |
RU2534680C1 (en) * | 2013-11-25 | 2014-12-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Turbomachine rotor |
EP3141706A1 (en) * | 2015-09-09 | 2017-03-15 | General Electric Technology GmbH | Steam turbine stage measurement system and a method therefor |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE281C (en) * | 1877-07-03 | E. VOSSKÖHLER, Werkstätten-Vorsteher der Bergisch-Märkischen Eisenbahn in Düsseldorf | Device for emergency signals on railroad cars | |
GB586200A (en) * | 1944-07-21 | 1947-03-11 | Karl Baumann | Improvements in bladed drum-type rotor constructions operating under high temperature conditions |
US2622789A (en) * | 1948-06-08 | 1952-12-23 | Curtiss Wright Corp | Turbine expansion section construction |
US2962256A (en) * | 1956-03-28 | 1960-11-29 | Napier & Son Ltd | Turbine blade shroud rings |
US2992809A (en) * | 1960-05-20 | 1961-07-18 | Allis Chalmers Mfg Co | Tandem compound steam turbine |
FR1404212A (en) * | 1964-08-12 | 1965-06-25 | Bbc Brown Boveri & Cie | Shock wave machine |
US3391904A (en) * | 1966-11-02 | 1968-07-09 | United Aircraft Corp | Optimum response tip seal |
US3514112A (en) * | 1968-06-05 | 1970-05-26 | United Aircraft Corp | Reduced clearance seal construction |
GB1238405A (en) * | 1969-06-04 | 1971-07-07 |
-
1970
- 1970-08-14 GB GB3917370A patent/GB1316452A/en not_active Expired
-
1971
- 1971-08-09 US US00169994A patent/US3709637A/en not_active Expired - Lifetime
- 1971-08-11 DE DE2140337A patent/DE2140337C3/en not_active Expired
- 1971-08-13 FR FR7129652A patent/FR2102268B1/fr not_active Expired
- 1971-08-13 JP JP46061123A patent/JPS5217180B1/ja active Pending
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170058675A1 (en) * | 2015-08-31 | 2017-03-02 | Rolls-Royce Corporation | Low diameter turbine rotor clamping arrangement |
US10100642B2 (en) * | 2015-08-31 | 2018-10-16 | Rolls-Royce Corporation | Low diameter turbine rotor clamping arrangement |
Also Published As
Publication number | Publication date |
---|---|
FR2102268B1 (en) | 1974-03-29 |
JPS5217180B1 (en) | 1977-05-13 |
DE2140337B2 (en) | 1975-04-10 |
DE2140337C3 (en) | 1975-11-20 |
FR2102268A1 (en) | 1972-04-07 |
US3709637A (en) | 1973-01-09 |
DE2140337A1 (en) | 1973-07-26 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PLE | Entries relating assignments, transmissions, licences in the register of patents | ||
PCNP | Patent ceased through non-payment of renewal fee | ||
PCPE | Delete 'patent ceased' from journal |
Free format text: 4961 PAGE 1066 |
|
PCNP | Patent ceased through non-payment of renewal fee |