Patent US4012167A successfully refreshed from Google Patents.
US4012167A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbomachinery vane or blade with cooled platforms
Assignee: RTX Corp
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Filing: 1975-10-14
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Granted: 1977-03-15
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Expires: 1995-10-14
Abstract
Abstract A turbomachinery vane or blade with a cooled platform including a coolant cavity in said platform into which a plurality of cooling fluid impingement jets are projected to impinge against the platform wall and then flow along the platform wall after impingement for cooling thereof and eventual discharge from the cooling cavity along the platform surface. A plurality of dam members extend into the cooling cavity adjacent the impingement jets so as to isolate the impingement jets from cross-flow and channel flow effects from the cooling fluid passing through the cooling cavity following impingement.
Inventors
- 👤 Melvin Lee Noble
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 06:32
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/187; F05; F05D; F05D2240/00; F05D2240/10; F05D2240/80; F05D2240/81; F05D2260/00; F05D2260/20; F05D2260/201
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
236 words
A turbomachinery airfoil member adapted to be supported to extend across a heated gas passage in turbomachinery and having: A. a platform located at one end of the airfoil member and positioned and shaped to form a boundary of the heated gas passage and including: 1. a heated gas passage defining wall member, B. means to cool said platform including: 1. wall means shaped to define a chamber of shallow height and including and extending substantially parallel to said wall member, 2. at least two cooling fluid inlet apertures in said wall means opposite said platform wall member, said apertures being selectively shaped and oriented to direct a stream of cooling fluid therethrough to impinge against said platform wall member in response to pressure differential across said inlet apertures, 3. at least one cooling fluid exhaust aperture in said wall means selectively positioned to define a cooling fluid flow path across said chamber from said inlet apertures to said exhaust aperture, and 4. dam means extending across the height of said chamber adjacent said inlet apertures and being selectively shaped to cooperate with said wall means to define a cavity separate from but communicating with the cooling fluid flow path to protect the impingement jets of cooling fluid passing through said inlet apertures from cross-flow interference from the cooling fluid passing through the cooling fluid flow path until impingement against said platform wall member has occurred.
Claim 2
Dependent Claim
236 words
A turbomachinery airfoil member adapted to be supported to extend across a heated gas passage in turbomachinery and having: A. a platform located at one end of the airfoil member and positioned and shaped to form a boundary of the heated gas passage and including: 1. a heated gas passage defining wall member, B. means to cool said platform including: 1. wall means shaped to define a chamber of shallow height and including and extending substantially parallel to said wall member, 2. at least two cooling fluid inlet apertures in said wall means opposite said platform wall member, said apertures being selectively shaped and oriented to direct a stream of cooling fluid therethrough to impinge against said platform wall member in response to pressure differential across said inlet apertures, 3. at least one cooling fluid exhaust aperture in said wall means selectively positioned to define a cooling fluid flow path across said chamber from said inlet apertures to said exhaust aperture, and 4. dam means extending across the height of said chamber adjacent said inlet apertures and being selectively shaped to cooperate with said wall means to define a cavity separate from but communicating with the cooling fluid flow path to protect the impingement jets of cooling fluid passing through said inlet apertures from cross-flow interference from the cooling fluid passing through the cooling fluid flow path until impingement against said platform wall member has occurred.
Claim 3
Dependent Claim
30 words
An airfoil member according to claim 1 wherein said dam means are oriented to be substantially normal to the cooling flow path between said inlet apertures and said exhaust aperture.
Claim 4
Dependent Claim
93 words
An airfoil member according to claim 2 wherein said exhaust aperture constitutes the inlet to a channel passing through the platform and terminating in the platform heated gas passage boundary defining surface so that the platform is cooled by a combination of impingement cooling due to the cooling air impingement jets impinging against the platform wall member, convection cooling due to the cooling air passing along the cooling fluid flow path and through the channel, and film cooling due to the discharge of the cooling air from the channel in the platform surface.
Claim 5
Dependent Claim
185 words
A turbomachinery airfoil member adapted to be supported to extend across a heated gas passage in turbomachinery and having a platform at one of its ends having: A. a first wall member extending along and forming the boundary of the hot gas passage, B. a second wall member in spaced relation to said first wall member to form a main cooling fluid flow passage therebetween, C. means joining said first and second wall members to form a platform cooling fluid chamber, D. at least one cooling fluid impingement hole extending through said second wall member and sized and oriented to project a jet of cooling fluid across said cooling chamber and against said first wall member in response to pressure differential thereacross, E. flow dam means partially enveloping said impingement hole and extending across said cooling chamber and communicating with said main cooling fluid flow passage and oriented so as to isolate the impingement jet from the coolant flow through said main cooling fluid flow passage and so that the cooling fluid from the impingement jet will enter said main cooling flow passage following impingement.
Claim 6
Dependent Claim
185 words
A turbomachinery airfoil member adapted to be supported to extend across a heated gas passage in turbomachinery and having a platform at one of its ends having: A. a first wall member extending along and forming the boundary of the hot gas passage, B. a second wall member in spaced relation to said first wall member to form a main cooling fluid flow passage therebetween, C. means joining said first and second wall members to form a platform cooling fluid chamber, D. at least one cooling fluid impingement hole extending through said second wall member and sized and oriented to project a jet of cooling fluid across said cooling chamber and against said first wall member in response to pressure differential thereacross, E. flow dam means partially enveloping said impingement hole and extending across said cooling chamber and communicating with said main cooling fluid flow passage and oriented so as to isolate the impingement jet from the coolant flow through said main cooling fluid flow passage and so that the cooling fluid from the impingement jet will enter said main cooling flow passage following impingement.
Claim 7
Dependent Claim
73 words
An airfoil member according to claim 4 and including at least one channel extending through said platform and communicating with said cooling chamber and terminating in the first wall member boundary defining surface so that cooling fluid flow from said main cooling fluid flow passage will be discharged therethrough after passage through said chamber to convectively cool the platform in passing through the channel and to film cool the platform boundary defining surface.
Claim 8
Dependent Claim
97 words
An airfoil member according to claim 5 wherein said second wall member is a plate member having a plurality of apertures extending therethrough and along one side of the cooling chamber, wherein said connecting means is a raised lip projecting from said first wall member and to which said plate member is attached, and wherein said flow dam means includes a plurality of flow dams extending across said cooling chamber and spaced to form a plurality of impingement chambers therebetween each communicating with at least one of said apertures and with said main cooling fluid flow passage.
Claim 9
Dependent Claim
101 words
An airfoil member according to claim 6 having an airfoil section projecting from the platform and having a pressure side, a suction side, a leading edge, a trailing edge and a chord extending between the leading edge and the trailing edge, and further wherein said cooling chamber extends along one side of the airfoil member, wherein said main cooling fluid flow passage extends substantially the full dimension of the cooling chamber, and wherein said flow dams project from one side of the cooling chamber toward the center thereof and substantially normal to the main cooling fluid flow passage and opening thereinto.
Claim 10
Independent Claim
82 words
The method of cooling the wall of the end platform of a turbomachinery gas path airfoil member comprising the steps of: A. causing one or more jets of coolant to impinge against the platform wall, causing the cooling fluid to flow along the platform wall following impingement as a layer of cooling air, and protecting the impingement jet from the cooling fluid flow layer so as to prevent degradation of the impingement jet by cross-flow effects from the cooling fluid flow layer.
Claim 11
Independent Claim
82 words
The method of cooling the wall of the end platform of a turbomachinery gas path airfoil member comprising the steps of: A. causing one or more jets of coolant to impinge against the platform wall, causing the cooling fluid to flow along the platform wall following impingement as a layer of cooling air, and protecting the impingement jet from the cooling fluid flow layer so as to prevent degradation of the impingement jet by cross-flow effects from the cooling fluid flow layer.
Claim 12
Dependent Claim
28 words
A turbomachinery vane or blade having: A. an airfoil section adapted to extend across a hot gas passage, B. a platform attached to the airfoil section and having:
Claim 13
Dependent Claim
28 words
A turbomachinery vane or blade having: A. an airfoil section adapted to extend across a hot gas passage, B. a platform attached to the airfoil section and having:
Claim 14
Dependent Claim
98 words
an inner surface constituting the boundary of the hot gas passage, and 2. an outer surface on the opposite side of the platform from the inner surface, C. means to cool said platform including: 1. means to cause a jet of coolant to impinge against said platform outer surface to cool the platform by impingement cooling, 2. means to cause the coolant to flow along the platform outer surface following impingement to cool the platform by convection cooling, and 3. means to isolate the impingement jet from the coolant air flowing along the platform outer surface following impingement.
Claim 15
Dependent Claim
98 words
an inner surface constituting the boundary of the hot gas passage, and 2. an outer surface on the opposite side of the platform from the inner surface, C. means to cool said platform including: 1. means to cause a jet of coolant to impinge against said platform outer surface to cool the platform by impingement cooling, 2. means to cause the coolant to flow along the platform outer surface following impingement to cool the platform by convection cooling, and 3. means to isolate the impingement jet from the coolant air flowing along the platform outer surface following impingement.
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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) | 1980-03-14 | 1980-09-13 | 1981-03-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-03-14 | 1984-09-13 | 1985-03-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-03-14 | 1988-09-13 | 1989-03-15 | $7700.00 | Window Closed / Lapsed |