Patent US4302153A successfully refreshed from Google Patents.
US4302153A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rotor blade for a gas turbine engine
Assignee: Rolls Royce PLC
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Filing: 1980-01-15
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Granted: 1981-11-24
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Expires: 2000-01-15
Abstract
Abstract A rotor blade for a gas turbine engine comprises an aerofoil, shank portion and a root by which the remainder of the blade may be supported from a rotor disc. Cooling for the aerofoil is provided by passages in the leading portion of the aerofoil which are fed with cooling air from an entry aperture and a sealed liquid cooling circuit which contains a cooling liquid. This circuit comprises a liquid feed passage adjacent the trailing edge of the aerofoil and connected adjacent the tip of the aerofoil with a vapor return passage, both passages communicating with a sealed cavity within the shank of the blade. In operation the cooling fluid (e.g. metallic sodium) flows under the influence of centrifugal and other forces along the feed passage, is vaporized and returns to the cavity via the return passage. The cavity acts as a condenser for the fluid.
Inventors
- 👤 Henry Tubbs
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 07:18
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
153 words
A rotor blade for a gas turbine engine comprising an aerofoil, a shank portion and a root adapted to engage with a rotor disc so as to support the aerofoil via the shank, and cooling means for the aerofoil comprising passages in the leading portion of the aerofoil, a cooling air entry aperture connected to the passages for the flow of cooling air therethrough, and a sealed cooling fluid circuit in the trailing portion of the aerofoil containing a quantity of cooling fluid and comprising a liquid feed passage closely adjacent to the trailing edge, and a vapour return passage forward of said liquid feed passage, wall portions extending between the flanks of the blade which at least partly divide said feed from said return passage, and a sealed cavity within the shank of the blade communicating with the feed and return passages and adapted to operate as a condenser of the vapour.
Claim 2
Dependent Claim
153 words
A rotor blade for a gas turbine engine comprising an aerofoil, a shank portion and a root adapted to engage with a rotor disc so as to support the aerofoil via the shank, and cooling means for the aerofoil comprising passages in the leading portion of the aerofoil, a cooling air entry aperture connected to the passages for the flow of cooling air therethrough, and a sealed cooling fluid circuit in the trailing portion of the aerofoil containing a quantity of cooling fluid and comprising a liquid feed passage closely adjacent to the trailing edge, and a vapour return passage forward of said liquid feed passage, wall portions extending between the flanks of the blade which at least partly divide said feed from said return passage, and a sealed cavity within the shank of the blade communicating with the feed and return passages and adapted to operate as a condenser of the vapour.
Claim 3
Dependent Claim
24 words
A rotor blade as claimed in claim 1 and comprising a broken wall which divides said liquid feed passage from said vapour return passage.
Claim 4
Dependent Claim
35 words
A rotor blade as claimed in claim 2 and in which the breaks in said wall form passages which are directed in operation to divert any liquid in the return passage into the feed passage.
Claim 5
Dependent Claim
37 words
A rotor blade as claimed in claim 1 and comprising separating means where the return passage enters the sealed cavity, the separating means in operation tending to prevent liquid from the cavity feeding into the return passage.
Claim 6
Dependent Claim
28 words
A rotor blade as claimed in claim 4 and in which said separating means comprises a raised lip at the junction between said return passage and said cavity.
Claim 7
Dependent Claim
31 words
A rotor blade as claimed in claim 1 and in which said cavity has an internal surface adpated to improve heat transfer from the cavity to the shank of the blade.
Claim 8
Dependent Claim
16 words
A rotor blade as claimed in claim 1 in which the cooling fluid comprises metallic sodium.
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) | 1984-11-23 | 1985-05-25 | 1985-11-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-11-23 | 1989-05-25 | 1989-11-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-11-23 | 1993-05-25 | 1993-11-24 | $7700.00 | Window Closed / Lapsed |