EP0206683A2
Expired / Lapsed
EP
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Internal bypass gas turbine engines with blade cooling
Assignee: University of Dayton
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Filing: 1986-06-13
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Granted: —
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Expires: 2006-06-13
Abstract
Abstract In relation to Fig. 2 of the drawing, a gas turbine with a compressor (18) and a turbine (20), bypasses a portion of the cool air from the compressor (18) into the turbine (20) through a conduit (30, 32), which conduit delivers the cool air to the inlet (33) of the turbine blades (26) so that the cool air (36) flows along the suction side of the turbine blades and maintains a stable flow condition with respect to the hot gases (37) along the pressure side of the turbine blades, with the result that the turbine blades are cooled by the cool air through the conduit (30).
Inventors
- 👤 John E. Minardi
- 👤 Hans P. Von Ohain
- 👤 Maurice O. Lawson
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-11-05 14:21
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F02; F02C; F02C7/00; F02C7/12; F02C7/125; F02C7/16; F02C7/18; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
94 words
A gas turbine having a compression section (18), a combustion section (24), and a turbine section (20), in which, in operation, a portion of cool air is bypassed from said compression section, characterized by a conduit (30) for conveying bypassed cool air to the inlet region of said turbine section for applying cool air to the suction side of the turbine blades (26) while maintaining Taylor-stable flow conditions of the said cool air at said turbine and of the hot gases from said combustion section so as to define a relatively stable interface therebetween.
Claim 2
Dependent Claim
94 words
A gas turbine having a compression section (18), a combustion section (24), and a turbine section (20), in which, in operation, a portion of cool air is bypassed from said compression section, characterized by a conduit (30) for conveying bypassed cool air to the inlet region of said turbine section for applying cool air to the suction side of the turbine blades (26) while maintaining Taylor-stable flow conditions of the said cool air at said turbine and of the hot gases from said combustion section so as to define a relatively stable interface therebetween.
Claim 3
Dependent Claim
60 words
A gas turbine as claimed in claim 1 in which said compression section and turbine section include a common rotor (112) in a case (132) and characterized by the fact that said conduit is defined by said rotor between the compressor vanes (110) and the turbine (120), and an annular wall (130) on the case (132) forming a bypass region.
Claim 4
Dependent Claim
76 words
A gas turbine as claimd in claim 1 in which said compression section is axially separated from said turbine section, defined by separate rotating components, and characterized by the fact that said conduit is a passageway (32) extending in a generally axially direction from an inlet adjacent the tips of the blades (22) in the compressor section for acceptance of bypass air to an outlet adjacent the roots of the blades (26) in said turbine section.
Claim 5
Dependent Claim
84 words
A gas turbine as claimed in claim 1 in which said turbine secton includes a rotor, a plurality of vanes thereon, said vanes being configured with an entry radial section (110) and a discharge axial section (120), and the gases from said combustion section are applied to said axial section, characterized by the fact that said conduit provides cool air to the inlet of said radial section whereby said cool air flows along the suction side of said turbine blades for cooling said blades.
Claim 6
Dependent Claim
26 words
A gas turbine as claimed in any preceding claim in which between five and fifteen percent of total compressor airflow is bypassed through said conduit means.
Claim 7
Dependent Claim
65 words
A a gas turbine as claimed in any preceding claim in which the total pressure of hot gases from the combustion section is considerably greater than the total pressure of the cold air from said conduit so that said cold air forms a flow sheet on the suction side of . the turbine blade passages with minimum intermixing with hot gases from the combustion section.
Claim 8
Dependent Claim
49 words
A gas turbine as claimed in claim 4 in which said compressor section and turbine section are mounted on a common monorotor, and characterized by said conduit is defined by a wall (130) at a radially outermost part of the monorotor between said compression section and said turbine section.
Claim 9
Independent Claim
82 words
A method of operating a gas turbine characterized by steps of bleeding a quantity of cold air from an inlet region and directing said cold air to the radially inner or root ends of the turbine blades while simultaneously applying hot combustion gases to said turbine blades at a radially outer portion thereof, in such a manner so said respective gas flows have minimum intermixing at said turbine blade with the cold air following closely the suction side of the turbine blades.
Claim 10
Independent Claim
82 words
A method of operating a gas turbine characterized by steps of bleeding a quantity of cold air from an inlet region and directing said cold air to the radially inner or root ends of the turbine blades while simultaneously applying hot combustion gases to said turbine blades at a radially outer portion thereof, in such a manner so said respective gas flows have minimum intermixing at said turbine blade with the cold air following closely the suction side of the turbine blades.
Claim 11
Dependent Claim
77 words
A method as claimed in claim 8 in which a gas turbine has a bypass passageway, including the steps of intercepting the relatively cooler air from said bypass passage way, providing a conduit for conveying said cooler air to the inlet region of the turbine blades adjacent the radially inner ends thereof, and applying hot gases to the radially outer portions of said turbine blades so that the respective gas flows form a relatively stable interface therebetween.
References Cited (Backward Citations)
No citation records indexed.
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