Patent US3647313A successfully refreshed from Google Patents.
US3647313A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engines with compressor rotor cooling
Assignee: General Electric Co
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Filing: 1970-06-01
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Granted: 1972-03-07
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Expires: 1990-06-01
Abstract
Abstract The disclosure shows a system for cooling the rotor of an axial flow compressor incorporated in a gas turbine engine. Air is ducted from the first compressor stage discharge into the interior of the rotor. This cooling air flows to the downstream end of the rotor and is then ducted back into the compressor inlet.
Inventors
- 👤 Bernard L Koff
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 23:28
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/02; F01D5/08; F01D5/081; F01D5/084; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
207 words
A multistage axial flow compressor comprising: a casing defining the outer bounds of an annular flow path for air being pressurized, said casing having vanes disposed in axially spacEd circumferential rows, a rotor defining the inner bounds of the annular flow path, said rotor having blades mounted thereon in axially spaced circumferential rows, said blade rows projecting between said vane rows and cooperating therewith to progressively pressurize air in said flow path, said rotor including a generally cylindrical shell having thin-walled end sections, with at least a portion of said blades being mounted on said shell, said generally cylindrical shell including axially spaced annular discs projecting into the interior thereof and, relatively thin annular spacers separating said discs, said blades being mounted around the peripheries of at least some of the discs, said discs in combination with said end sections and each other respectively, forming annular chambers, means for directing air from a region of the flow path having a given pressure level, into the most upstream of said chambers within the shell''s interior, and means for ducting said air from the downstream end portion of the shell''s interior to and into a region of the flow path having a lower pressure level than said given level.
Claim 2
Dependent Claim
207 words
A multistage axial flow compressor comprising: a casing defining the outer bounds of an annular flow path for air being pressurized, said casing having vanes disposed in axially spacEd circumferential rows, a rotor defining the inner bounds of the annular flow path, said rotor having blades mounted thereon in axially spaced circumferential rows, said blade rows projecting between said vane rows and cooperating therewith to progressively pressurize air in said flow path, said rotor including a generally cylindrical shell having thin-walled end sections, with at least a portion of said blades being mounted on said shell, said generally cylindrical shell including axially spaced annular discs projecting into the interior thereof and, relatively thin annular spacers separating said discs, said blades being mounted around the peripheries of at least some of the discs, said discs in combination with said end sections and each other respectively, forming annular chambers, means for directing air from a region of the flow path having a given pressure level, into the most upstream of said chambers within the shell''s interior, and means for ducting said air from the downstream end portion of the shell''s interior to and into a region of the flow path having a lower pressure level than said given level.
Claim 3
Dependent Claim
60 words
A multistage axial flow compressor as in claim 1 wherein, said ducting means comprises a central tube extending between the end sections of said shell, said tube having openings into the most downstream chamber within said shell, means for blocking the downstream end of said tube and passageway means from the upstream end of said tube to said flow path.
Claim 4
Dependent Claim
57 words
A multistage axial flow compressor as in claim 1 wherein, the directing means include passageways extending generally radially through the upstream end section of said shell at a distance adjacent to inner bounds of said flow path, and impeller means for directing the air radially inwardly approximately to the diameter of the bore of the adjacent disc.
Claim 5
Dependent Claim
55 words
An axial flow compressor as in claim 4 wherein, the impeller means are secured to the upstream end section and have a shroud secured thereto in spaced relation from said upstream end section, and further wherein the inlet portions of the passageways through the upstream end section are curved in the direction of rotor rotation.
Claim 6
Dependent Claim
153 words
A multistage axial flow compressor as in claim 1 wherein, the end sections of the rotor are conical, a further disc is secured to and spaced upstream from the upstream conical end section by an annular spacer and a plurality of blades are mounted around the periphery of said further disc to form the first rotor stage of the compressor, sealing means are provided between the rotor and the vane row downstream of said first rotor stage, and the air-directing means comprise passageways through said upstream end section downstream of the named sealing means, and the ducting means comprises a central tube extending between the end sections of said shell, said tube having openings into the most downstream chamber within said shell, means for blocking the downstream end of said tube and passageway means extending through the upstream end of said tube, through said rotor, to the upstream side of said further disc.
Claim 7
Dependent Claim
40 words
A multistage axial flow compressor as in claim 5 wherein, impeller means are provided for directing air radially inwardly, from the passageways through the end section of said shell, approximately to the diameter of the bore of the adjacent disc.
Claim 8
Dependent Claim
77 words
An axial flow compressor as in claim 6 wherein, the upstream conical end section is formed by a conical portion formed integrally with a stub shaft and an outer conical portion formed integrally with said adjacent disc, said conical portions and the spacer of said further disc having radial flanges bolted together with the flange of the inner conical portion between the other two flanges, and the air-directing passageways are formed in said inner conical portion flange.
Claim 9
Dependent Claim
45 words
An axial flow compressor as in claim 7 wherein, a conical shroud is secured to said impeller means and extends in spaced relationship from the inner surface of said inner conical portion from the outer conical portion flange to a diameter spaced from said tube.
Claim 10
Dependent Claim
73 words
A multistage axial flow compressor as in claim 8 wherein, the entrances to the radial passageways through said inner cone flange are curved in the direction of rotor rotation, and wherein the impeller means include a plurality of angularly spaced impellers extending from said inner cone flange to the inner diameter of the shroud cone and a plurality of shorter impellers extending from said cone flange partially toward said shroud cone inner diameter.
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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) | 1975-03-07 | 1975-09-06 | 1976-03-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-03-07 | 1979-09-06 | 1980-03-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-03-07 | 1983-09-06 | 1984-03-07 | $7700.00 | Window Closed / Lapsed |