US4162136A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Cooled blade for a gas turbine engine
Assignee: Rolls Royce PLC
•
Filing: 1975-04-01
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Granted: 1979-07-24
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Expires: 1995-04-01
Abstract
Abstract A cooled blade for a gas turbine engine comprises an aerofoil portion having a longitudinally extending hollow. An air entry tube is mounted within the hollow and is pressed against a locating surface within the hollow by a resilient member such as a spring tube.
Inventors
- 👤 Roger J. Parkes
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 09:38
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/187; F01D5/188; F01D5/189; F05; F05D; F05D2300/00; F05D2300/50; F05D2300/501
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
103 words
A cooled blade for a gas turbine engine comprising an aerofoil portion having a cavity therein, a cooling air entry tube within the cavity, said cavity having an interior surface with a part which forms a locating surface for said tube, a longitudinally extending depression formed in the outer surface of said cooling air entry tube, a further part of the interior surface of the cavity having a longitudinally extending depression facing the depression formed in the outer surface of said cooling air entry tube, and a resilient tube trapped between the depressions in said cooling air entry tube and said further part.
Claim 2
Dependent Claim
103 words
A cooled blade for a gas turbine engine comprising an aerofoil portion having a cavity therein, a cooling air entry tube within the cavity, said cavity having an interior surface with a part which forms a locating surface for said tube, a longitudinally extending depression formed in the outer surface of said cooling air entry tube, a further part of the interior surface of the cavity having a longitudinally extending depression facing the depression formed in the outer surface of said cooling air entry tube, and a resilient tube trapped between the depressions in said cooling air entry tube and said further part.
Claim 3
Dependent Claim
22 words
A cooled blade as claimed in claim 1 and in which said locating surface has a plurality of locating protrusions formed thereon.
Claim 4
Dependent Claim
28 words
A cooled blade as claimed in claim 1 and in which said resilient member and said cooling air entry tube are also retained in the blade by brazing.
Claim 5
Dependent Claim
34 words
A cooled blade as claimed in claim 1 and in which said cooling air entry tube has apertures in its wall through which cooling air may blow on to the interior of said cavity.
Claim 6
Dependent Claim
43 words
A cooled blade as claimed in claim 4 and in which said cavity is formed in the leading part of said aerofoil portion, the remainder of the aerofoil portion being provided with a sinuous passage formed therein for the passage of cooling air.
Claim 7
Dependent Claim
24 words
A cooled blade as claimed in claim 1 and comprising a cap metallurgically bonded to the tip of the blade to cover said cavity.
Claim 8
Dependent Claim
36 words
A cooled blade as claimed in claim 1 in which said resilient tube comprises a tube whose wall is made of a resilient material and has a longitudinally extending slot cut therethrough along its entire length.
References Cited (Backward Citations)
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US3628885A
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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) | 1982-07-23 | 1983-01-22 | 1983-07-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-07-23 | 1987-01-22 | 1987-07-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-07-23 | 1991-01-22 | 1991-07-24 | $7700.00 | Window Closed / Lapsed |