Patent US3695091A successfully refreshed from Google Patents.
Patent EP0076340A1 successfully refreshed from Google Patents.
US4116584A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Device for extending the working range of axial flow compressors
Assignee: Gutehoffnungshutte Sterkrade AG
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Filing: 1977-02-04
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Granted: 1978-09-26
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Expires: 1997-02-04
Abstract
Abstract In an axial flow compressor including a rotor wheel having a plurality of rotating blades mounted thereon, said rotor being arranged to rotate about a central axis of the compressor, there is provided an aerodynamically profiled ring arranged concentrically to the compressor axis in front or upstream of the plurality of rotating blades in order to define between an outer surface of the profiled ring and an inner wall of the compressor casing an annular flow channel which converges in the direction of flow through the compressor. A plurality of stationary blades are located upstream of the profiled ring.
Inventors
- 👤 Karl Bammert
- 👤 Rudolf Staude
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 17:51
CPC Classifications
F; F04; F04D; F04D29/00; F04D29/40; F04D29/52; F04D29/54; F04D29/541; F04D19/00; F04D19/02; F04D19/028; F04D27/00; F04D27/02; F04D29/26; F04D29/32; F04D29/321; F04D29/324; Y; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
139 words
An axial flow compressor comprising a rotor having a plurality of rotating blades mounted thereon, a central compressor axis about which said rotor rotates, a casing including an inner casing wall within which said rotor is located, said casing wall defining together with said rotor an annular compressor flow conduit converging in the direction of axial flow through said compressor, a plurality of stationary blades located in said compressor flow conduit upstream of said rotating blades, and a ring of airfoil cross section arranged concentrically to said compressor axis and located in said compressor flow conduit upstream of said rotating blades between said rotating blades and said stationary blades, said airfoil ring being configured and arranged to define together with said casing wall an annular flow channel therebetween converging in the direction of flow through said compressor flow conduit.
Claim 2
Dependent Claim
139 words
An axial flow compressor comprising a rotor having a plurality of rotating blades mounted thereon, a central compressor axis about which said rotor rotates, a casing including an inner casing wall within which said rotor is located, said casing wall defining together with said rotor an annular compressor flow conduit converging in the direction of axial flow through said compressor, a plurality of stationary blades located in said compressor flow conduit upstream of said rotating blades, and a ring of airfoil cross section arranged concentrically to said compressor axis and located in said compressor flow conduit upstream of said rotating blades between said rotating blades and said stationary blades, said airfoil ring being configured and arranged to define together with said casing wall an annular flow channel therebetween converging in the direction of flow through said compressor flow conduit.
Claim 3
Dependent Claim
39 words
A compressor according to claim 1 wherein said ring is mounted in said flow conduit by a plurality of radially extending support elements attached between said inner casing wall and said ring to extend through said annular flow channel.
Claim 4
Dependent Claim
51 words
A compressor according to claim 1 wherein said annular flow channel includes an annular inlet and an annular outlet, said ring and said inner casing wall being arranged such that the ratio between the area of said inlet and the area of said outlet is between about 1.3 and 2.0 .
Claim 5
Dependent Claim
66 words
A compressor according to claim 1 wherein said ring comprises an upstream edge located adjacent said stationary blades and wherein said rotating blades comprise a maximum radial length extending from said rotor, said upstream edge of said ring being located a distance from the central axis of said rotor which is between about 65 to 70 percent of said maximum radial length of said rotating blades.
Claim 6
Dependent Claim
71 words
A compressor according to claim 1 wherein said ring comprises an upstream edge located adjacent but spaced from said stationary blades by one gap, and a downstream edge located adjacent but spaced from said rotating blades by another gap, said ring having an axial width extending between said upstream and downstream edges, with the size of both said gaps being at least 10 percent of said axial width of said ring.
Claim 7
Dependent Claim
20 words
A compressor according to claim 2 including a retaining ring connecting said support elements to extend from said casing wall.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1981-09-25 | 1982-03-27 | 1982-09-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-09-25 | 1986-03-27 | 1986-09-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-09-25 | 1990-03-27 | 1990-09-26 | $7700.00 | Window Closed / Lapsed |