Patent US6283705B1 successfully refreshed from Google Patents.
US6283705B1
Expired / Lapsed
US
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Variable vane with winglet
Assignee: Rolls Royce North American Technologies Inc
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Filing: 1999-02-26
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Granted: 2001-09-04
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Expires: 2019-02-26
Abstract
Abstract A gas turbine engine variable vane having a winglet integrally formed therewith. In one embodiment, the variable vane includes a winglet attached to one end so as to reduce endwall losses resulting from air leakage from the high-pressure side to the low-pressure side of the airfoil. The winglet substantially increases the width of the endwall gap thereby reducing the loss associated with the vortex flow caused by leakage of gas from the pressure side to the section side of the airfoil. In another aspect the winglet runs along the airfoil thereby increasing stiffness and acting as a bracing strut to increase the resonant frequency of the airfoil.
Inventors
- 👤 Edward Claude Rice
- 👤 Robert Anthony Ress, Jr.
- 👤 Jeffrey Lister Hansen
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 17:16
CPC Classifications
F; F01; F01D; F01D17/00; F01D17/10; F01D17/12; F01D17/14; F01D17/16; F01D17/162; F04; F04D; F04D29/00; F04D29/40; F04D29/52; F04D29/54; F04D29/56; F04D29/563; F05; F05D; F05D2240/00; F05D2240/80; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 38
Claim 1
Independent Claim
131 words
A gas turbine engine variable vane, comprising: an airfoil having an outer surface extending spanwise between an inner and an outer end and further extending streamwise between a leading edge and a trailing edge; a first button coupled to one of said ends of said airfoil; and a first winglet positioned along one of said ends of said airfoil and extending from said outer surface, wherein said first winglet is configured so as to increase the width of a first endwall gap defined by said one of said ends and a first surface of the gas turbine engine, the width of the first winglet along a first portion substantially adjacent the leading edge being greater than the width of the first winglet along a second portion substantially adjacent the trailing edge.
Claim 2
Dependent Claim
131 words
A gas turbine engine variable vane, comprising: an airfoil having an outer surface extending spanwise between an inner and an outer end and further extending streamwise between a leading edge and a trailing edge; a first button coupled to one of said ends of said airfoil; and a first winglet positioned along one of said ends of said airfoil and extending from said outer surface, wherein said first winglet is configured so as to increase the width of a first endwall gap defined by said one of said ends and a first surface of the gas turbine engine, the width of the first winglet along a first portion substantially adjacent the leading edge being greater than the width of the first winglet along a second portion substantially adjacent the trailing edge.
Claim 3
Dependent Claim
53 words
The variable vane of claim 1 , wherein said airfoil has a rotational axis extending spanwise between said inner and outer ends, said first button is at said outer end of said airfoil, and a first spindle extending outward in the spanwise direction from said first button and co-linear with said rotational axis.
Claim 4
Dependent Claim
51 words
The variable vane of claim 2 , further including a second button at said inner end of said airfoil, and a second spindle extending outward in the spanwise direction from said second button and co-linear with said rotational axis, and wherein said winglet is integrally formed with one of said buttons.
Claim 5
Dependent Claim
99 words
The variable vane of claim 2 , which further includes a second button at said inner end of said airfoil, and a second spindle adjacent said second button and extending inward in the spanwise direction and co-linear with said rotational axis; and, wherein said first winglet runs along a chord length between the leading and trailing edges of said airfoil and increases the stiffness of said variable vane, said first winglet being integrally formed with said second button and wherein said first winglet has a thickness between about 0.030 to about 0.060 inches so as to minimize aerodynamic blockage.
Claim 6
Dependent Claim
18 words
The variable vane of claim 1 , wherein said variable vane is a low aspect ratio variable vane.
Claim 7
Dependent Claim
16 words
The variable vane of claim 1 , wherein said variable vane is a cantilevered variable vane.
Claim 8
Dependent Claim
32 words
The variable vane of claim 1 , wherein said winglet runs along a chord length between the leading and trailing edge of said airfoil to increase the stiffness of said variable vane.
Claim 9
Dependent Claim
24 words
The variable vane of claim 7 , wherein said winglet is between about 0.030 to about 0.060 inches so as to minimize aerodynamic blockage.
Claim 10
Dependent Claim
45 words
The variable vane of claim 1 , wherein said first winglet is at said inner end, and further including a second winglet running along said outer end and extending from said outer surface, said first button being coupled to said outer end of said airfoil.
Claim 11
Dependent Claim
41 words
The variable vane of claim 9 , which further includes a first fillet connecting between the intersection of said inner end and said first winglet, and a second fillet incorporated at the intersection of said outer end and said first button.
Claim 12
Dependent Claim
100 words
The variable vane of claim 9 , which further includes a second button at said inner end of said airfoil, and a second spindle adjacent said second button and extending inward in the spanwise direction and co-linear with said rotational axis; and, wherein said first and second winglets run along a chord length between the leading and trailing edges of said airfoil, increasing the stiffness of said variable vane, said first and second winglets being integrally formed with said second and first buttons respectively, and said first and second winglets having a thickness between about 0.030 to about 0.060 inches.
Claim 13
Dependent Claim
34 words
The variable vane of claim 11 , wherein said airfoil has a pressure side and a suction side, and wherein said first and second winglets extend from said suction side and said pressure side.
Claim 14
Dependent Claim
30 words
The variable vane of claim 11 , wherein said airfoil has a pressure side and a suction side, and wherein said first and second winglets extend from said suction side.
Claim 15
Dependent Claim
30 words
The variable vane of claim 11 , wherein said airfoil has a pressure side and a suction side, and wherein said first and second winglets extend from said pressure side.
Claim 16
Dependent Claim
27 words
The variable vane of claim 1 , wherein said airfoil has a pressure side and a suction side, and wherein said winglet is on said suction side.
Claim 17
Dependent Claim
31 words
The variable vane of claim 1 , wherein said airfoil has a pressure side and a suction side, and wherein said winglet is on said suction side and said pressure side.
Claim 18
Dependent Claim
27 words
The variable vane of claim 1 , wherein said airfoil has a pressure side and a suction side and wherein said winglet is on said pressure side.
Claim 19
Dependent Claim
148 words
A gas turbine engine variable vane, comprising: an airfoil with an outer surface having a pressure side and a suction side, said airfoil including opposed inner and outer ends and opposed upstream and downstream ends; a first boss mounted to said inner end; and a first winglet formed with said first boss on said inner end, wherein said first winglet is configured so as to reduce loss associated with a vortex flow caused by a leakage of a gas from said pressure side to said suction side of said airfoil by forcing the vortex away from said outer surface, said first winglet being configured so as to increase the width of a first endwall gap defined by said inner end of said airfoil and a first surface of the gas turbine engine, the width of the first winglet substantially tapering from the upstream end to the downstream end.
Claim 20
Dependent Claim
148 words
A gas turbine engine variable vane, comprising: an airfoil with an outer surface having a pressure side and a suction side, said airfoil including opposed inner and outer ends and opposed upstream and downstream ends; a first boss mounted to said inner end; and a first winglet formed with said first boss on said inner end, wherein said first winglet is configured so as to reduce loss associated with a vortex flow caused by a leakage of a gas from said pressure side to said suction side of said airfoil by forcing the vortex away from said outer surface, said first winglet being configured so as to increase the width of a first endwall gap defined by said inner end of said airfoil and a first surface of the gas turbine engine, the width of the first winglet substantially tapering from the upstream end to the downstream end.
Claim 21
Dependent Claim
41 words
The variable vane of claim 18 , wherein said first winglet runs along a chord length between the upstream and downstream ends of said inner end, and said first winglet acting as a brace increasing the stiffness of said variable vane.
Claim 22
Dependent Claim
27 words
The variable vane of claim 19 , wherein said first winglet has a thickness between about 0.030 to about 0.060 inches so as to minimize aerodynamic blockage.
Claim 23
Dependent Claim
141 words
The variable vane of claim 19 , wherein said first winglet has a thickness between about 0.030 to about 0.060; further including a first fillet connecting between the intersection of said inner end with said first winglet, a second boss mounted to said outer end of said airfoil, a second fillet connecting between the intersection of said outer end with said second boss, a first spindle adjacent said first boss extending inward from said inner end and centered on the rotational axis of said airfoil, and a second spindle adjacent said second boss extending outward from said outer end and centered on the rotational axis of said airfoil; and said first winglet being configured so as to increase the width of a first endwall gap defined by said inner end of said airfoil and a surface of the gas turbine engine.
Claim 24
Dependent Claim
65 words
The variable vane of claim 21 , further including a second winglet formed with said second boss and mounted to the outer end of said airfoil, said second winglet being configured to increase the width of a second endwall gap defined by said outer end of said airfoil and a second surface of the gas turbine engine to which said variable vane is adjustably mounted.
Claim 25
Dependent Claim
50 words
The variable vane of claim 18 , which further includes a first fillet connecting between the intersection of said inner end with said first boss and said first winglet, and a second fillet connecting between the intersection of said outer end with a second boss mounted to said outer end.
Claim 26
Dependent Claim
65 words
The variable vane of claim 18 , wherein said airfoil has a rotational axis extending between said opposed inner and outer ends, and which further includes a first spindle extending inward from said inner end and centered on the rotational axis of said airfoil, and further includes a second spindle extending outward from said outer end and centered on the rotational axis of said airfoil.
Claim 27
Dependent Claim
70 words
The variable vane of claim 18 , further including a second winglet formed with a second boss, said second boss being mounted to said outer end of said airfoil, said second winglet being configured so as to increase the width of a second endwall gap defined by said outer end of said airfoil and a second surface of the gas turbine engine to which said variable vane is adjustably mounted.
Claim 28
Dependent Claim
18 words
The variable vane of claim 18 , wherein said variable vane is a low aspect ratio variable vane.
Claim 29
Dependent Claim
41 words
The combination of claim 12 , further including a second boss at said outer end of said airfoil, said first boss being coupled to said inner end of said airfoil and said first winglet being integrally formed with said first boss.
Claim 30
Dependent Claim
136 words
A combination, comprising: a gas turbine engine including a mechanical housing; a plurality of variable vanes disposed within a fluid flow path within said mechanical housing, each of said plurality of vanes comprising: an airfoil with a pressure side and a suction side, said airfoil having an outer surface extending spanwise between an inner end and an outer end and further extending streamwise between a leading end and a trailing end, said airfoil having a rotational axis extending spanwise between said inner and outer ends; a first boss coupled to one of said inner and outer ends of said airfoil; and, a first winglet running along one of said inner and outer ends of said airfoil and extending from said outer surface, wherein said winglet does not extend upstream of said leading end of said airfoil.
Claim 31
Dependent Claim
136 words
A combination, comprising: a gas turbine engine including a mechanical housing; a plurality of variable vanes disposed within a fluid flow path within said mechanical housing, each of said plurality of vanes comprising: an airfoil with a pressure side and a suction side, said airfoil having an outer surface extending spanwise between an inner end and an outer end and further extending streamwise between a leading end and a trailing end, said airfoil having a rotational axis extending spanwise between said inner and outer ends; a first boss coupled to one of said inner and outer ends of said airfoil; and, a first winglet running along one of said inner and outer ends of said airfoil and extending from said outer surface, wherein said winglet does not extend upstream of said leading end of said airfoil.
Claim 32
Dependent Claim
37 words
The combination of claim 28 , wherein said first winglet runs along a chord length between the leading and trailing ends of said airfoil, said winglet acting as a brace increasing the stiffness of said variable vane.
Claim 33
Dependent Claim
23 words
The combination of claim 28 , wherein said winglet has a thickness between 0.030 to 0.060 inches so as to minimize aerodynamic blockage.
Claim 34
Dependent Claim
39 words
The combination of claim 28 , wherein each of said variable vanes is adjustably connected to said mechanical housing by a spindle extending outward from said outer end of said airfoil, said spindle being co-linear with the rotational axis.
Claim 35
Dependent Claim
25 words
The combination of claim 31 , wherein said first winglet is at said inner end, and further including a second winglet on said outer end.
Claim 36
Dependent Claim
32 words
The combination of claim 28 , wherein said first winglet is at said inner end, and further including a first fillet connecting between the intersection of said inner end and said winglet.
Claim 37
Dependent Claim
21 words
The combination of claim 28 , wherein at least one of said variable vanes is a low aspect ratio variable vane.
Claim 38
Dependent Claim
19 words
The combination of claim 28 , wherein at least one of said variable vanes is a cantilevered variable vane.
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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) | 2004-09-03 | 2005-03-05 | 2005-09-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2008-09-03 | 2009-03-05 | 2009-09-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2012-09-03 | 2013-03-05 | 2013-09-04 | $7700.00 | Window Closed / Lapsed |