Patent US3742706A successfully refreshed from Google Patents.
US3742706A
Expired / Lapsed
US
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Dual flow cooled turbine arrangement for gas turbine engines
Assignee: General Electric Co
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Filing: 1971-12-20
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Granted: 1973-07-03
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Expires: 1991-12-20
Abstract
Abstract Turbine blading for a gas turbine engine includes a dual source of turbine cooling airflow wherein a portion of the high pressure compressor discharge airflow is directed to cool the most critical temperature areas of the turbine blade and a portion of the low pressure compressor interstage airflow is directed to cool the less critical temperature areas of the same turbine blade. The invention herein described was made in the course of or under a contract or subcontract thereunder (or grant) with the Department of the Navy.
Inventors
- 👤 N Klompas
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 11:31
CPC Classifications
F; F28; F28D; F28D21/00; F28D21/0001; F28D21/0003; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F01D5/085; F01D5/087; F01D5/12; F01D5/14; F01D5/18; F28F; F28F5/00; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
234 words
In a gas turbine engine having a compressor, combustor and turbine in serial flow relation, a dual flow cooled turbine arrangement comprises: first means for bleeding a portion of the compressor air-flow at a point intermediate the inlet and discharge ends of the compressor, second Means for bleeding a portion of the compressor airflow at a location downstream from the first bleed means where the pressure of the compressor airflow is greater than at the first means, a turbine wheel drivably connecting the compressor, a plurality of blades disposed in circumferentially spaced relation about the periphery of the turbine wheel wherein the interior of the airfoil vane of each blade includes a first hollow compartment for receiving compressor bleed cooling airflow from the first bleed means and directing the bleed air to cool those areas of the airfoil vane subject to the impingement of the lower pressures of hot gas from the combustor and a second hollow compartment for receiving the higher pressure compressor bleed cooling airflow from the second bleed means and directing the higher pressure bleed air to cool those areas of the airfoil vane subject to the impingement of the higher pressures of hot gas from the combustor, means for directing the compressor bleed airflow from the first bleed means to the turbine blades, and means for directing the compressor bleed airflow from the second bleed means to the turbine blades.
Claim 2
Dependent Claim
234 words
In a gas turbine engine having a compressor, combustor and turbine in serial flow relation, a dual flow cooled turbine arrangement comprises: first means for bleeding a portion of the compressor air-flow at a point intermediate the inlet and discharge ends of the compressor, second Means for bleeding a portion of the compressor airflow at a location downstream from the first bleed means where the pressure of the compressor airflow is greater than at the first means, a turbine wheel drivably connecting the compressor, a plurality of blades disposed in circumferentially spaced relation about the periphery of the turbine wheel wherein the interior of the airfoil vane of each blade includes a first hollow compartment for receiving compressor bleed cooling airflow from the first bleed means and directing the bleed air to cool those areas of the airfoil vane subject to the impingement of the lower pressures of hot gas from the combustor and a second hollow compartment for receiving the higher pressure compressor bleed cooling airflow from the second bleed means and directing the higher pressure bleed air to cool those areas of the airfoil vane subject to the impingement of the higher pressures of hot gas from the combustor, means for directing the compressor bleed airflow from the first bleed means to the turbine blades, and means for directing the compressor bleed airflow from the second bleed means to the turbine blades.
Claim 3
Dependent Claim
28 words
The dual flow cooled turbine arrangement of claim 1 wherein the second bleed means is arranged to bleed a portion of the compressor airflow discharged from the compressor.
Claim 4
Dependent Claim
121 words
The dual flow cooled turbine arrangement of claim 2 wherein the means for bleeding a portion of the compressor interstage airflow and directing the airflow back to the turbine blade includes: a bleed port from the compressor at a point intermediate the inlet and discharge ends of the compressor; a hollow drive shaft interconnecting the turbine and compressor, the hollow interior of which is in flow communication with the bleed port for receiving the compressor interstage bleed cooling air and directing the cooling airflow aft to the turbine; and a radially extending annular first plenum through the turbine wheel for receiving the compressor interstage bleed cooling air and directing the cooling air to the first hollow compartment of each airfoil vane.
Claim 5
Dependent Claim
117 words
The dual flow cooled turbine arrangement of claim 3 wherein the means for bleeding a portion of the compressor discharge airflow and directing the airflow back to the turbine blade includes: an interior cylindrical partition interposed radially between the combustor and interconnecting shaft defining an axially extending annular second plenum between the partition and interconnecting shaft, a bleed port through the cylindrical partition for bleeding a portion of the compressor discharge airflow wherein the compressor discharge bleed air flows the length of the axially extending plenum and the interconnecting shaft operates as a heat exchanger providing for the transfer of heat from the higher temperature compressor discharge bleed air to the lower temperature compressor interstage bleed air.
Claim 6
Dependent Claim
58 words
The dual flow cooled turbine of claim 4 including an annular seal member sealingly engaged to the turbine wheel and turbine blades so as to define a third plenum chamber therebetween and including a plurality of inlet ports for directing the discharge cooling airflow through the third plenum and into the second hollow compartment of each airfoil vane.
Claim 7
Dependent Claim
180 words
The dual flow cooled turbine of claim 2 wherein means for attaching the blades to the turbine wheel comprises: two circumferential and axially spaced dovetail rails extending radially outward from the periphery of the turbine wheel with each rail thickened at the outer radial end to provide outwardly extending shoulders wherein slots are provided through the shoulders to accommodate individual blade insertion; a semi-circular root portion extending in a substantially inward radial direction from the base of the airfoil vane of each blade; a dovetail root portion extending radially inward from the interior of the semi-circular root portion from a point substantially intermediate the lateral ends of the semi-cIrcle and thickened at the inner radial end to provide outwardly extending shoulders, tang members extending radially inward from the respective ends of the semi-circular root portions such that upon blade insertion within the slots, each blade may be circumferentially slid so that the outwardly extending shoulders of the dovetail root engage the inwardly facing shoulders of the opposing rails and the tangs respectively engage the outwardly facing shoulders of the rails.
Claim 8
Dependent Claim
188 words
The dual flow cooled turbine of claim 6 wherein: the turbine wheel includes a radially extending annular first plenum through the turbine wheel for receiving the compressor interstage bleed cooling air whereupon the interstage bleed cooling air may be centrifuged along the radial extent of the first plenum and dumped from the outer periphery of the turbine wheel into the area confined by the inner surface of the semi-circular root portion, an annular seal member is sealingly engaged to the turbine wheel and blade root portions so as to define a second plenum chamber therebetween including a plurality of inlet ports for directing the compressor discharge bleed cooling air into the second plenum, the semi-circular root portions include first passages therethrough communicating from the first hollow compartment of each airfoil vane to the inner surface of each semi-circular root portion for receiving and directing interstage bleed cooling air into the first compartment, and second passages therethrough communicating from the second hollow compartment of each airfoil vane to the lateral edge of each semi-circular root portion for receiving and directing compressor discharge bleed cooling air into the second compartment.
Claim 9
Dependent Claim
183 words
In a gas turbine engine having a dual source of cooling flow means for attaching the blades to the turbine wheel comprise: two circumferentially and axially spaced dovetail rails extending radially outward from the periphery of the turbine wheel with each rail thickened at the outer radial end to provide outwardly extending shoulders wherein slots are provided through the shoulders to accommodate individual blade insertion; a semi-circular root portion extending in a substantially inward radial direction from the base of the airfoil vane of each blade; a dovetail root portion extending radially inward from the interior of the semi-circular root portion from a point substantially intermediate the lateral ends of the semi-circle and thickened at the inner radial end to provide outwardly extending shoulders; tang members extending radially inward from the respective ends of the semi-circular root portions such that upon blade insertion within the slots, each blade may be circumferentially slid so that the outwardly extending shoulders of the dovetail root engage the inwardly facing shoulders of the opposing rails and the tangs respectively engage the outwardly facing shoulders of the rails.
Claim 10
Dependent Claim
183 words
In a gas turbine engine having a dual source of cooling flow means for attaching the blades to the turbine wheel comprise: two circumferentially and axially spaced dovetail rails extending radially outward from the periphery of the turbine wheel with each rail thickened at the outer radial end to provide outwardly extending shoulders wherein slots are provided through the shoulders to accommodate individual blade insertion; a semi-circular root portion extending in a substantially inward radial direction from the base of the airfoil vane of each blade; a dovetail root portion extending radially inward from the interior of the semi-circular root portion from a point substantially intermediate the lateral ends of the semi-circle and thickened at the inner radial end to provide outwardly extending shoulders; tang members extending radially inward from the respective ends of the semi-circular root portions such that upon blade insertion within the slots, each blade may be circumferentially slid so that the outwardly extending shoulders of the dovetail root engage the inwardly facing shoulders of the opposing rails and the tangs respectively engage the outwardly facing shoulders of the rails.
References Cited (Backward Citations)
US849992A
Cited
US2401826A
Cited
GB827264A
Cited
US2988325A
Cited
US3034298A
Cited
US3453825A
Cited
US3635586A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-07-02 | 1977-01-01 | 1977-07-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-07-02 | 1981-01-01 | 1981-07-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-07-02 | 1985-01-01 | 1985-07-03 | $7700.00 | Window Closed / Lapsed |