Patent EP0112003A1 successfully refreshed from Google Patents.
EP0112003A1
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Rotor blade form for the first stage of a combustion turbine
Assignee: Westinghouse Electric Corp
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Filing: 1983-10-19
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Granted: —
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Expires: 2003-10-19
Abstract
Abstract A rotor blade for a land-based combustion turbine includes an airfoil portion, a root portion, and a platform. The airfoil portion comprises a unique and specific geometric and dimensional range shape structured to minimize aerodynamic losses and maximize turbine efficiency.
Inventors
- 👤 David Lee Brown
- 👤 William Kilby Fentress
- 👤 Melvin Dallas Taylor
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-08 17:20
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/141; F05; F05D; F05D2240/00; F05D2240/20; F05D2240/30; F05D2240/301; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
161 words
An airfoil blade for a cooled first stage rotor of a land-based combustion turbine capable of driv - ing an electric generator to generate electric power in the range of one hundred megawatts, said blade comprising: airfoil portion having a leading edge and a trailing edge with concave and convex surfaces therebetween providing a smooth airfoil surface, a root portion for affixing said blade to a turbine rotor, a platform portion joining said airfoil portion to said root portion, said airfoil portion having: a gradually decreasing cross-sectional area with increasing radius; a maximum cross-sectional thickness which between said convex and concave sides decreases with increasing radius from approximately 1.0 inch to approximately 0.78 inch; a cross-sectional width which decreases with increasing radius from approximately 3.853 inches to approximately 3.240 inches; a chord which decreases with increasing radius from approximately 4.051 to 3.965; said leading edge having a. radius which decreases with increasing radius from approximately 0.141 inch to approximately 0.102 inch.
Claim 2
Dependent Claim
161 words
An airfoil blade for a cooled first stage rotor of a land-based combustion turbine capable of driv - ing an electric generator to generate electric power in the range of one hundred megawatts, said blade comprising: airfoil portion having a leading edge and a trailing edge with concave and convex surfaces therebetween providing a smooth airfoil surface, a root portion for affixing said blade to a turbine rotor, a platform portion joining said airfoil portion to said root portion, said airfoil portion having: a gradually decreasing cross-sectional area with increasing radius; a maximum cross-sectional thickness which between said convex and concave sides decreases with increasing radius from approximately 1.0 inch to approximately 0.78 inch; a cross-sectional width which decreases with increasing radius from approximately 3.853 inches to approximately 3.240 inches; a chord which decreases with increasing radius from approximately 4.051 to 3.965; said leading edge having a. radius which decreases with increasing radius from approximately 0.141 inch to approximately 0.102 inch.
Claim 3
Dependent Claim
35 words
A blade according to claim 1 wherein said airfoil portion has a tip and sixteen cooling channels of substantially circular cross-section extending generally radially from said root portion through said airfoil portion to said tip.
Claim 4
Dependent Claim
23 words
A blade according to claim 1, wherein said trailing edge radius increases with increasing blade radius from approximately 0.074 inches to 0.075 inches.
Claim 5
Dependent Claim
40 words
A blade according to claim 2, wherein said coolant channels are generally linear and the location of said coolant channels are defined by X-Y coordinates in preselected cross reference planes as defined by the holes location table in the specification.
Claim 6
Dependent Claim
53 words
A blade according to claim 1 wherein the .airfoil surface along said convex and concave sides is defined by a series of X-Y coordinates in each of a plurality of preselected cross reference planes spaced along the span of said airfoil portion as defined by the airfoil coordinate points table in the specification.
Claim 7
Dependent Claim
53 words
A blade according to claim 4 wherein the airfoil surface along said convex and concave sides is defined by a series of X-Y coordinates in each of a plurality of preselected cross reference planes spaced along the span of said airfoil portion as defined by the airfoil coordinate points table in the specification.
References Cited (Backward Citations)
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