US3781129A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Cooled airfoil
Assignee: Motors Liquidation Co
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Filing: 1972-09-15
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Granted: 1973-12-25
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Expires: 1992-09-15
Abstract
Abstract A hollow air-cooled turbine blade or vane includes a liner for bringing cooling air into the blade and discharging it through two cooling air exhaust tubes disposed near the interior of the leading edge and extending spanwise of the blade. These tubes define between them a slot nozzle for discharge of air from the liner for impingement cooling of the leading edge. The exhaust tubes have air entrance holes adjacent the leading edge. The pressure drop to cause the circulation of the air out through the tubes is caused by centrifugal force or pressure drop across the stage or both.
Inventors
- 👤 R Aspinwall
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 22:36
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/187; F01D5/188; F01D5/189
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
109 words
A cooled fluid-directing element for a turbomachine comprising, in combination, a wall defining a hollow airfoil having two faces and a leading edge joining the faces, means for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at one end of the airfoil, the exhaust tubes defining between them a slot nozzle for discharge of the cooling gas from the conducting means toward the interior of the leading edge, and the exhaust tubes defining means for entry of the cooling gas into the tubes from near the leading edge.
Claim 2
Dependent Claim
109 words
A cooled fluid-directing element for a turbomachine comprising, in combination, a wall defining a hollow airfoil having two faces and a leading edge joining the faces, means for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at one end of the airfoil, the exhaust tubes defining between them a slot nozzle for discharge of the cooling gas from the conducting means toward the interior of the leading edge, and the exhaust tubes defining means for entry of the cooling gas into the tubes from near the leading edge.
Claim 3
Dependent Claim
131 words
A cooled fluid-directing rotor blade element for a turbomachine comprising, in combination, a wall defining a hollow airfoil having two faces and a leading edge joining the faces, the airfoil having a base adapted for connection to a rotor and having a tip remote from the base, means for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at the tip end of the airfoil, the exhaust tubes defining between them a slot nozzle for discharge of the cooling gas from the conducting means toward the interior of the leading edge, and the exhaust tubes defining means for entry of the cooling gas into the tubes from near the leading edge.
Claim 4
Dependent Claim
131 words
A cooled fluid-directing rotor blade element for a turbomachine comprising, in combination, a wall defining a hollow airfoil having two faces and a leading edge joining the faces, the airfoil having a base adapted for connection to a rotor and having a tip remote from the base, means for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at the tip end of the airfoil, the exhaust tubes defining between them a slot nozzle for discharge of the cooling gas from the conducting means toward the interior of the leading edge, and the exhaust tubes defining means for entry of the cooling gas into the tubes from near the leading edge.
Claim 5
Dependent Claim
146 words
A cooled fluid-directing nozzle vane installation for a turbomachine comprising, in combination, a wall defining a hollow nozzle vane airfoil having two faces and a leading edge joining the faces, means for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at one end of the airfoil, the exhaust tubes defining between them a slot nozzle for discharge of the cooling gas from the conducting means toward the interior of the leading edge, and the exhaust tubes defining means for entry of the cooling gas into the tubes from near the leading edge, the means for conducting the cooling gas into the element being subjected to pressure upstream of the nozzle vane and the exhaust tube outlet being subjected to pressure downstream of the nozzle vane.
Claim 6
Dependent Claim
146 words
A cooled fluid-directing nozzle vane installation for a turbomachine comprising, in combination, a wall defining a hollow nozzle vane airfoil having two faces and a leading edge joining the faces, means for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at one end of the airfoil, the exhaust tubes defining between them a slot nozzle for discharge of the cooling gas from the conducting means toward the interior of the leading edge, and the exhaust tubes defining means for entry of the cooling gas into the tubes from near the leading edge, the means for conducting the cooling gas into the element being subjected to pressure upstream of the nozzle vane and the exhaust tube outlet being subjected to pressure downstream of the nozzle vane.
Claim 7
Dependent Claim
126 words
A cooled fluid-directing element for a turbomachine comprising, in combination, a wall defining a hollow airfoil having two faces and a leading edge joining the faces, means including a blade liner for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at one end of the airfoil, the exhaust tubes defining the leading edge portion of the blade liner and defining between them a slot nozzle for discharge of the cooling gas from the liner toward the interior of the leading edge, and the exhaust tubes having ports distributed along the tubes for entry of the cooling gas into the tubes from near the leading edge.
Claim 8
Dependent Claim
126 words
A cooled fluid-directing element for a turbomachine comprising, in combination, a wall defining a hollow airfoil having two faces and a leading edge joining the faces, means including a blade liner for conducting a cooling gas into the airfoil, two cooling gas exhaust tubes disposed adjacent the interior of the leading edge and extending spanwise of the airfoil to an outlet at one end of the airfoil, the exhaust tubes defining the leading edge portion of the blade liner and defining between them a slot nozzle for discharge of the cooling gas from the liner toward the interior of the leading edge, and the exhaust tubes having ports distributed along the tubes for entry of the cooling gas into the tubes from near the leading edge.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-12-24 | 1977-06-25 | 1977-12-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-12-24 | 1981-06-25 | 1981-12-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-12-24 | 1985-06-25 | 1985-12-25 | $7700.00 | Window Closed / Lapsed |