US4008977A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Compressor bleed system
Assignee: RTX Corp
•
Filing: 1975-09-19
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Granted: 1977-02-22
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Expires: 1995-09-19
Abstract
Abstract Methods and apparatus for flowing cooling air from the compressor section to the turbine section of a gas turbine engine are disclosed. Cooling air from the compressor is flowed radially inward through the compressor drum cavity and thence axially rearward along the rotor shaft to the turbine. Vortex pressure losses in the drum cavity are diminished to enable effective utilization of a lower pressure, lower temperature cooling air source. The use of air from the lower pressure, lower temperature source improves the overall engine operating efficiency while maintaining turbine cooling rates which are consonant with durable operation of the engine.
Inventors
- 👤 Wayne Myron Brown
- 👤 Joseph Carmen Manente, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 21:34
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/12; F02C7/16; F02C7/18; F04; F04D; F04D29/00; F04D29/26; F04D29/32; F04D29/321; F04D27/00; F04D27/02; F04D27/0207; F04D27/0215
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
121 words
A method for flowing cooling air from the compressor section of a gas turbine engine to the turbine section wherein said engine has a compressor drum and a drum cavity which are located radially inward of the flow path for the working medium gases and a rotor shaft which connects the compressor drum to the turbine, comprising the steps of: bleeding air from the flow path for the working medium gases in the compressor section; discharging the bleed air into the drum cavity in a tangential direction relative to the drum which is opposite to the direction of drum rotation; and flowing the discharged air radially inward through the drum cavity and axially rearward to the turbine section of the engine.
Claim 2
Independent Claim
121 words
A method for flowing cooling air from the compressor section of a gas turbine engine to the turbine section wherein said engine has a compressor drum and a drum cavity which are located radially inward of the flow path for the working medium gases and a rotor shaft which connects the compressor drum to the turbine, comprising the steps of: bleeding air from the flow path for the working medium gases in the compressor section; discharging the bleed air into the drum cavity in a tangential direction relative to the drum which is opposite to the direction of drum rotation; and flowing the discharged air radially inward through the drum cavity and axially rearward to the turbine section of the engine.
Claim 3
Dependent Claim
37 words
The invention according to claim 1 wherein the air is discharged into the compressor drum at an absolute tangential velocity which approaches zero to minimize the vortex pressure loss on the air flowing through the drum cavity.
Claim 4
Dependent Claim
112 words
In a gas turbine engine of the type having a turbine section and a compression section wherein the compression section has incorporated therein radially inward of the flow path for the working medium gases a cylindrical drum and a drum cavity through which cooling air is flowable from the flow path in the compressor to the turbine for cooling components of the turbine, the improvements comprising: means including a nozzle extending radially inward from said cylindrical drum for discharging compressor air from the medium flow path into the drum cavity at a tangential velocity with respect to the drum which is opposite in direction to the direction of rotation of the drum.
Claim 5
Dependent Claim
112 words
In a gas turbine engine of the type having a turbine section and a compression section wherein the compression section has incorporated therein radially inward of the flow path for the working medium gases a cylindrical drum and a drum cavity through which cooling air is flowable from the flow path in the compressor to the turbine for cooling components of the turbine, the improvements comprising: means including a nozzle extending radially inward from said cylindrical drum for discharging compressor air from the medium flow path into the drum cavity at a tangential velocity with respect to the drum which is opposite in direction to the direction of rotation of the drum.
Claim 6
Dependent Claim
39 words
The invention according to claim 1 wherein the air is discharged into the compressor drum cavity at an absolute tangential velocity which approaches zero to minimize the vortex pressure loss imposed upon the air flowing through the drum cavity.
Claim 7
Dependent Claim
30 words
The invention according to claim 3 wherein said nozzle is adapted to cause the air flowing therethrough to discharge in a direction which is substantially parallel to the tangent line.
Claim 8
Dependent Claim
37 words
The invention according to claim 5 wherein the air is discharged into the compressor drum at an absolute tangential velocity which approaches zero to minimize the vortex pressure loss on the air flowing through the drum cavity.
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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) | 1980-02-22 | 1980-08-23 | 1981-02-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-02-22 | 1984-08-23 | 1985-02-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-02-22 | 1988-08-23 | 1989-02-22 | $7700.00 | Window Closed / Lapsed |