US4826400A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Curvilinear turbine airfoil
Assignee: General Electric Co
•
Filing: 1986-12-29
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Granted: 1989-05-02
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Expires: 2006-12-29
Abstract
Abstract A turbomachinary airfoil in one form comprises a pressure side and a suction side curved circumferentially outward in the direction that the suction side faces. The invention is effective for reducing both radial and circumferential boundary layer pressure gradients thereby reducing airfoil aerodynamic losses. In another form of the invention the airfoil is a vane of a turbine vane assembly having an inner and outer shroud wherein the vane in addition to being curved is leaned circumferentially outward in the direction that the suction side faces.
Inventors
- 👤 Brent A. Gregory
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 05:57
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/141; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
33 words
A turbine vane comprising a pressure side and a suction side, wherein said airfoil is curved circumferentially outward in a first direction, said first direction being the direction which said suction side faces.
Claim 2
Dependent Claim
33 words
A turbine vane comprising a pressure side and a suction side, wherein said airfoil is curved circumferentially outward in a first direction, said first direction being the direction which said suction side faces.
Claim 3
Dependent Claim
17 words
The turbine vane of claim 1 wherein said turbine vane is also leaned in said first direction.
Claim 4
Dependent Claim
44 words
A turbine vane comprising a pressure side, a suction side, and a stacking line for defining the profile of said airfoil, wherein said stacking line is curved circumferentially outward in a first direction, said first direction being the direction which said suction side faces.
Claim 5
Dependent Claim
44 words
A turbine vane comprising a pressure side, a suction side, and a stacking line for defining the profile of said airfoil, wherein said stacking line is curved circumferentially outward in a first direction, said first direction being the direction which said suction side faces.
Claim 6
Dependent Claim
15 words
The turbine vane of claim 3 wherein said stacking line is shaped in an arc.
Claim 7
Dependent Claim
17 words
The turbine vane of claim 4 wherein said turbine vane is also leaned in said first direction.
Claim 8
Dependent Claim
42 words
The turbine vane of claim 4 including an turbine vane midspan wherein said stacking line shaped in an arc is defined by a radius having an origin located on a line perpendicular to the tangent of said arc at said airfoil midspan.
Claim 9
Dependent Claim
51 words
A turbine vane assembly comprising an inner shroud, an outer shroud, and a turbine vane mounted between said shrouds, said vane including a pressure side and a suction side, wherein said vane is curved circumferentially outward in a first direction, said first direction is the direction which said suction side faces.
Claim 10
Dependent Claim
51 words
A turbine vane assembly comprising an inner shroud, an outer shroud, and a turbine vane mounted between said shrouds, said vane including a pressure side and a suction side, wherein said vane is curved circumferentially outward in a first direction, said first direction is the direction which said suction side faces.
Claim 11
Dependent Claim
44 words
A turbine vane assembly comprising an inner shroud, an outer shroud, and a turbine vane mounted between said shrouds, said vane including a pressure side, a suction side, and a stacking line, wherein said stacking line is curved circumferentially outward in said first direction.
Claim 12
Dependent Claim
44 words
A turbine vane assembly comprising an inner shroud, an outer shroud, and a turbine vane mounted between said shrouds, said vane including a pressure side, a suction side, and a stacking line, wherein said stacking line is curved circumferentially outward in said first direction.
Claim 13
Dependent Claim
14 words
The turbine vane assembly of claim 8 wherein said stacking line is arc shaped.
Claim 14
Dependent Claim
17 words
The turbine vane assembly of claim 9 wherein said airfoil is also leaned in said first direction.
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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) | 1992-05-01 | 1992-10-31 | 1993-05-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-05-01 | 1996-10-31 | 1997-05-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-05-01 | 2000-10-31 | 2001-05-02 | $7700.00 | Window Closed / Lapsed |