Patent US3874650A successfully refreshed from Google Patents.
US5201796A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine arrangement
Assignee: RTX Corp
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Filing: 1991-10-15
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Granted: 1993-04-13
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Expires: 2011-10-15
Abstract
Abstract A separate low pressure shaft and a high pressure shaft are axially aligned. The low pressure shaft is at one end and carries the low pressure compressor and the low pressure turbine, and is connected to the electric generator. The high pressure shaft carries the high pressure compressor and the high pressure turbine. Only three bearing housings are required. Parts of the casing are horizontally split to simplify maintenance.
Inventors
- 👤 Robert L. Glinski
- 👤 Gary M. Perkins
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 10:29
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/12; F02C7/14; F02C7/141; F02C7/143; F02C7/1435; F02C3/00; F02C3/36; F02C7/06; F05; F05D; F05D2250/00; F05D2250/30; F05D2250/31; F05D2250/312; F05D2260/00; F05D2260/20; F05D2260/211; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
244 words
A gas turbine arrangement for a power system comprising: a low pressure shaft; a high pressure shaft; a low pressure compressor rotor on said low pressure shaft; a low pressure turbine rotor on said low pressure shaft; a high pressure compressor rotor on said high pressure shaft; a high pressure turbine rotor on said high pressure shaft; said low pressure shaft and said high pressure shaft axially aligned and longitudinally offset, establishing a low pressure shaft end and a high pressure shaft end; said low pressure compressor rotor and said low pressure turbine rotor on said low pressure shaft at the low pressure end; said high pressure compressor rotor and said high pressure turbine rotor on said high pressure shaft at said high pressure end; a power output unit connected to said low pressure shaft; said low pressure shaft and said high pressure shaft being independently rotatable; a first bearing comprising a journal and thrust bearing between static structure and said low pressure shaft at the outboard end of said low pressure shaft; a second bearing comprising a journal bearing between static structure and said low pressure shaft at the inboard end of said high pressure shaft; a third bearing comprising a roller bearing between the inboard end of said low pressure shaft and the inboard end of said high pressure shaft; and a fourth bearing comprising a ball and thrust bearing between static structure and the outboard end of said high pressure shaft.
Claim 2
Dependent Claim
244 words
A gas turbine arrangement for a power system comprising: a low pressure shaft; a high pressure shaft; a low pressure compressor rotor on said low pressure shaft; a low pressure turbine rotor on said low pressure shaft; a high pressure compressor rotor on said high pressure shaft; a high pressure turbine rotor on said high pressure shaft; said low pressure shaft and said high pressure shaft axially aligned and longitudinally offset, establishing a low pressure shaft end and a high pressure shaft end; said low pressure compressor rotor and said low pressure turbine rotor on said low pressure shaft at the low pressure end; said high pressure compressor rotor and said high pressure turbine rotor on said high pressure shaft at said high pressure end; a power output unit connected to said low pressure shaft; said low pressure shaft and said high pressure shaft being independently rotatable; a first bearing comprising a journal and thrust bearing between static structure and said low pressure shaft at the outboard end of said low pressure shaft; a second bearing comprising a journal bearing between static structure and said low pressure shaft at the inboard end of said high pressure shaft; a third bearing comprising a roller bearing between the inboard end of said low pressure shaft and the inboard end of said high pressure shaft; and a fourth bearing comprising a ball and thrust bearing between static structure and the outboard end of said high pressure shaft.
Claim 3
Dependent Claim
18 words
A gas turbine arrangement as in claim 1: a common bearing housing enclosing said second and third bearings.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1996-04-12 | 1996-10-12 | 1997-04-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2000-04-12 | 2000-10-12 | 2001-04-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2004-04-12 | 2004-10-12 | 2005-04-13 | $7700.00 | Window Closed / Lapsed |