US3756019A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine blade arrangement
Assignee: Individual
•
Filing: 1971-07-02
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Granted: 1973-09-04
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Expires: 1991-07-02
Abstract
Abstract A gas turbine is formed with a first and a second stage, the first stage contains wheels on which turbine blades are concentrically arranged around compressor blades and the second stage contains wheels on which turbine blades are concentrically arranged around webs. A combustion chamber is arranged to receive air after it has been compressed by the compressor blades in the first stage and has been guided but not further compressed by the webs in the second stage. After the compressed air is heated in the combustion chamber it passes over the turbine blades in the second stage and then over the turbine blades in the first stage. The turbine blades in the first stage are hollow and air is withdrawn from the compressor side in the first stage and passed into the interior of the turbine blades to cool them.
Inventors
- 👤 H Holzapfel
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 14:44
CPC Classifications
F; F02; F02C; F02C3/00; F02C3/04; F02C3/06; F01; F01D; F01D5/00; F01D5/02; F01D5/08; F02C3/073; Y; Y10; Y10S; Y10S415/00; Y10S415/914
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
212 words
A gas turbine comprising a stationary shaft, a plurality of first wheels mounted on said stationary shaft, each of said wheels comprising a circumferentially extending row of radially extending compressor blades and a circumferentially extending row of turbine blades concentrically disposed about and extendinG radially outwardly from the radially outer ends of said compressor blades, a combustion chamber arranged to receive air compressed in said compressor blades on said first wheels for heatinG the air and returning it for flow over said turbine blades on said first wheels, a driVen output shaft extending axially from said stationary shaft and located between said stationary shaft and on said output shaft, wherein the improvement comprises that: said second wheels on said drive shaft comprise a circumferentially arranged row of radially outwardly extending webs and a circumferentially arranged row of radially outwardly extending turbine blades concentrically disposed about and extending radially outwardly from said row of webs, said webs arranged to receive the compressed air from said compressor blades on said first wheels and to direct the air into said combustion chamber without effecting any additional compRession thereof from where the heated air is directed over said turbine blades on said second wheels prior to its passage over said turbine blades on said first wheels.
Claim 2
Dependent Claim
212 words
A gas turbine comprising a stationary shaft, a plurality of first wheels mounted on said stationary shaft, each of said wheels comprising a circumferentially extending row of radially extending compressor blades and a circumferentially extending row of turbine blades concentrically disposed about and extendinG radially outwardly from the radially outer ends of said compressor blades, a combustion chamber arranged to receive air compressed in said compressor blades on said first wheels for heatinG the air and returning it for flow over said turbine blades on said first wheels, a driVen output shaft extending axially from said stationary shaft and located between said stationary shaft and on said output shaft, wherein the improvement comprises that: said second wheels on said drive shaft comprise a circumferentially arranged row of radially outwardly extending webs and a circumferentially arranged row of radially outwardly extending turbine blades concentrically disposed about and extending radially outwardly from said row of webs, said webs arranged to receive the compressed air from said compressor blades on said first wheels and to direct the air into said combustion chamber without effecting any additional compRession thereof from where the heated air is directed over said turbine blades on said second wheels prior to its passage over said turbine blades on said first wheels.
Claim 3
Dependent Claim
87 words
A gas turbine, as set forth in claim 1, characterized in that turbine blades on said first wheels being hollow, an annular base member extending circumferentially around the radially inner ends of said turbine blades and the radially outer ends of said compressor blades of said first wheels and separating said turbine blades from said compressor blades, and said base member having bores extending therethrough from said compressor blade side to said turbine blade side with the bores communicating with the hollow interiors of said turbine blades.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-09-03 | 1977-03-05 | 1977-09-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-09-03 | 1981-03-05 | 1981-09-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-09-03 | 1985-03-05 | 1985-09-04 | $7700.00 | Window Closed / Lapsed |