US3709637A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engines
Assignee: SECR DEFENCE
•
Filing: 1971-08-09
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Granted: 1973-01-09
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Expires: 1991-08-09
Abstract
Abstract In order to minimize the variation in the sealing clearance between a turbine rotor and associated static structure at different temperatures of the engine the shaft connecting the turbine with its compressor is supported at its ends in roller bearings. A tubular member is introduced, which is made of a low expansion material, which is located at an upstream datum radial plane and which supports the shaft at a joint close to the turbine rotor. The expansion of the shaft between the upstream roller bearing and the joint does not therefore, affect the position of the turbine rotor.
Inventors
- 👤 J Petrie
- 👤 T Gardiner
- 👤 J Clampitt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 02:09
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/02; F01D5/00; F01D5/02; F01D5/026; F02; F02C; F02C7/00; F02C7/20; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
124 words
A gas turbine engine having a rotor member, a shaft, means for connecting the shaft and the rotor member, bearings for supporting the shaft with freedom for axial thermal expansion of the shaft, means for supporting a sealing member in static structure at a first radial plane of the engine, the rotor member being spaced from the sealing member by an axial sealing clearance, means for locating the shaft in static structure at a radial datum plane of the engine, said means comprising a member made of a material having a lower coefficient of thermal expansion than the shaft, means for connecting said member to the shaft and means for locating said member in static structure of the engine at said radial datum plane.
Claim 2
Dependent Claim
124 words
A gas turbine engine having a rotor member, a shaft, means for connecting the shaft and the rotor member, bearings for supporting the shaft with freedom for axial thermal expansion of the shaft, means for supporting a sealing member in static structure at a first radial plane of the engine, the rotor member being spaced from the sealing member by an axial sealing clearance, means for locating the shaft in static structure at a radial datum plane of the engine, said means comprising a member made of a material having a lower coefficient of thermal expansion than the shaft, means for connecting said member to the shaft and means for locating said member in static structure of the engine at said radial datum plane.
Claim 3
Dependent Claim
41 words
A gas turbine engine according to claim 1 and in which the rotor member is a turbine rotor, the shaft connects the turbine rotor to a compressor of the engine and the member which locates the shaft is a tubular member.
Claim 4
Dependent Claim
29 words
A gas turbine engine according to claim 1 and in which the member is located at said radial datum plane of the engine by means of a ball bearing.
Claim 5
Dependent Claim
29 words
A gas turbine engine according to claim 2 and in which the radial datum plane of the engine is upstream of the compressor to which said shaft is connected.
Claim 6
Dependent Claim
41 words
A gas turbine engine according to claim 1 and in which means are provided for bleeding air from a compressor of the engine and for passing said air over at least one surface of the member to control the temperature thereof.
Claim 7
Dependent Claim
56 words
A gas turbine engine according to claim 1 and in which the static structure comprises a casing of the engine and at least a portion of said casing between the first and second radial planes is made of a material having a lower coefficient of thermal expansion than the remainder of the casing between said planes.
Claim 8
Dependent Claim
63 words
A gas turbine engine according to claim 6 and in which at least a portion of the casing comprises an inner wall and an outer wall radially spaced therefrom, the outer wall supporting the sealing member and being made from said material, means being provided for supplying cooling air bled from a compressor of the engine to the space between the two walls.
Claim 9
Dependent Claim
38 words
A gas turbine engine according to claim 1 and in which the material having the relatively low thermal expansion is a nickel-cobalt-iron alloy with a coefficient of thermal expansion within the range 0.000004 to 0.000005 per degree Centigrade.
References Cited (Backward Citations)
US2622789A
Cited
US2962256A
Cited
US2992809A
Cited
US3391904A
Cited
US3514112A
Cited
GB1238405A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-01-09 | 1976-07-10 | 1977-01-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-01-09 | 1980-07-10 | 1981-01-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-01-09 | 1984-07-10 | 1985-01-09 | $7700.00 | Window Closed / Lapsed |