Patent US4177010A successfully refreshed from Google Patents.
US4177010A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Cooled rotor blade for a gas turbine engine
Assignee: Rolls Royce PLC
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Filing: 1978-03-22
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Granted: 1979-12-04
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Expires: 1998-03-22
Abstract
Abstract A cooled rotorblade has two separate cooling passages or series of passages in its aerofoil. One passage or series communicates with an aperture in the root or shank of the blade for the supply of cooling fluid while the other communicates with a hollow bush mounted in the shank to provide an inlet for cooling fluid. In addition to providing a cooling fluid inlet the bush serves to blank off an interconnection between the otherwise separate passages, the interconnection assisting the manufacturing process.
Inventors
- 👤 Terence M. Greaves
- 👤 Robert D. Summers
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 21:18
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/187
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
218 words
A cooled rotor blade for a gas turbine engine comprising: an integrally cast hollow aerofoil portion, hollow shank portion, and root portion, said aerofoil portion having a leading edge, a trailing edge, and convex and concave flanks, said aerofoil portion further having a plurality of chordal-spaced and spanwise partitions extending between the convex and concave flanks from adjacent its tip portion and terminating in and/or adjacent the hollow interior of said shank portion, a hollow bush extending transversely through said shank portion and having at least one end open to the exterior of the shank portion for receiving a cooling fluid, said hollow bush engaging at least two adjacent partitions to define at least one cooling passage separate from at least another cooling passage which communicates with the hollow interior of said shank portion, said bush having an aperture in its wall opening to a space between the at least two partitions for supplying cooling fluid to the said at least one cooling passage, and a cooling fluid entry aperture in at least one of said root portion and said shank portion communicating with the hollow interior of said shank portion, said last-mentioned cooling fluid entry aperture supplying cooling fluid to the hollow interior of said shank portion and then to the said at least another cooling passage.
Claim 2
Dependent Claim
218 words
A cooled rotor blade for a gas turbine engine comprising: an integrally cast hollow aerofoil portion, hollow shank portion, and root portion, said aerofoil portion having a leading edge, a trailing edge, and convex and concave flanks, said aerofoil portion further having a plurality of chordal-spaced and spanwise partitions extending between the convex and concave flanks from adjacent its tip portion and terminating in and/or adjacent the hollow interior of said shank portion, a hollow bush extending transversely through said shank portion and having at least one end open to the exterior of the shank portion for receiving a cooling fluid, said hollow bush engaging at least two adjacent partitions to define at least one cooling passage separate from at least another cooling passage which communicates with the hollow interior of said shank portion, said bush having an aperture in its wall opening to a space between the at least two partitions for supplying cooling fluid to the said at least one cooling passage, and a cooling fluid entry aperture in at least one of said root portion and said shank portion communicating with the hollow interior of said shank portion, said last-mentioned cooling fluid entry aperture supplying cooling fluid to the hollow interior of said shank portion and then to the said at least another cooling passage.
Claim 3
Dependent Claim
30 words
A cooled rotor blade as claimed in claim 1 in which said bush is open at both ends to the exterior of the shank portion for receiving the cooling fluid.
Claim 4
Dependent Claim
93 words
A cooled rotor blade as claimed in claim 1 in which said at least another passage includes a first passage portion adjacent the leading eadge of said aerofoil portion and a second passage portion adjacent the trailing edge of said aerofoil portion and in which said at least one passage separate from said at least another passage is intermediate said first passage portion and said second passage portion and receives a relatively lower pressure cooling fluid from said bush than said first and second passage portions receive from said cooling fluid entry aperture.
Claim 5
Dependent Claim
21 words
A cooled rotor blade as claimed in claim 3 in which said second passage portion adjacent said trailing edge is sinuous.
Claim 6
Dependent Claim
56 words
A cooled rotor blade as claimed in claim 1 in which said cooling fluid entry aperture in at least one of said root portion and said shank portion is in a base of said root portion and provides communication for cooling fluid to the interior of said shank portion and to said at least another passage.
Claim 7
Dependent Claim
50 words
A cooled rotor blade as claimed in claim 1 in which said cooling fluid entry aperture in at least one of said root portion and said shank portion is positioned solely within said shank portion and provides communication between the exterior thereof and the hollow interior of said shank portion.
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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) | 1982-12-03 | 1983-06-04 | 1983-12-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-12-03 | 1987-06-04 | 1987-12-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-12-03 | 1991-06-04 | 1991-12-04 | $7700.00 | Window Closed / Lapsed |