US4086022A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine with improved compressor casing for permitting higher air flow and pressure ratios before surge
Assignee: Rolls Royce PLC
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Filing: 1976-09-07
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Granted: 1978-04-25
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Expires: 1996-09-07
Abstract
Abstract A plurality of skewed slots of a particular shape are provided within a compressor casing adjacent at least one stage of compressor blade tips, the slots having an axial length greater than that of the adjacent blade tips. The slots are provided such that upon occurrence of compressor surge or stall, the stagnating air occurring about the blade row may be directed by the slots downstream of the compressor blade row back into the main stream of fluid passing through the compressor. By such an arrangement, the slots provide a compressor in which the air flow and pressure ratio may be increased before reaching compressor stall or surge.
Inventors
- 👤 Christopher Freeman
- 👤 Robert Rudolph Moritz
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 10:40
CPC Classifications
F; F04; F04D; F04D29/00; F04D29/66; F04D29/68; F04D29/681; F04D29/685; F01; F01D; F01D11/00; F01D11/08; F04D29/40; F04D29/52; F04D29/522; F04D29/526; Y; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
225 words
An axial flow compressor for a gas turbine engine comprising: a rotor having at least one blade row with an axis of rotation; a compressor casing having an internal cylindrical surface surrounding said at least one blade row, said compressor casing having at least one circumferential row of slots, each of said slots having side walls, a bottom wall and a helical angle of inclination to the axis of rotation of said at least one blade row, said slots being disposed within the internal cylindrical surface of said casing adjacent to said at least one blade row and said slots having an axial length substantially greater than that of said at least one blade row and terminating downstream of said at least one blade row, said helical angle of inclination of each of said slots to the axis of rotation of said at least one blade row being substantially the same angle as an exit angle of fluid leaving said at least one blade row, and said bottom wall of each of said slots having a concave shape which is of substantially aerodynamic form so that high pressure fluid entering each slot adjacent said blade row is ducted along said slot to a location downstream of said at least one blade row and directed back into a main stream of fluid passing through the compressor.
Claim 2
Dependent Claim
225 words
An axial flow compressor for a gas turbine engine comprising: a rotor having at least one blade row with an axis of rotation; a compressor casing having an internal cylindrical surface surrounding said at least one blade row, said compressor casing having at least one circumferential row of slots, each of said slots having side walls, a bottom wall and a helical angle of inclination to the axis of rotation of said at least one blade row, said slots being disposed within the internal cylindrical surface of said casing adjacent to said at least one blade row and said slots having an axial length substantially greater than that of said at least one blade row and terminating downstream of said at least one blade row, said helical angle of inclination of each of said slots to the axis of rotation of said at least one blade row being substantially the same angle as an exit angle of fluid leaving said at least one blade row, and said bottom wall of each of said slots having a concave shape which is of substantially aerodynamic form so that high pressure fluid entering each slot adjacent said blade row is ducted along said slot to a location downstream of said at least one blade row and directed back into a main stream of fluid passing through the compressor.
Claim 3
Dependent Claim
46 words
An axial flow compressor as claimed in claim 1 in which said side walls of each of said slots extend from said internal cylindrical surface of said casing at an angle to a radius of said casing extending through the axis of rotation of said rotor.
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) | 1981-04-24 | 1981-10-24 | 1982-04-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-04-24 | 1985-10-24 | 1986-04-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-04-24 | 1989-10-24 | 1990-04-25 | $7700.00 | Window Closed / Lapsed |