US3971210A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Start-up compressed air system for gas turbine engines
Assignee: Dresser Industries Inc
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Filing: 1975-01-22
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Granted: 1976-07-27
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Expires: 1995-01-22
Abstract
Abstract The system described herein utilizes a constant speed compressor to augment a service compressor that is an integral part of a gas turbine engine to assure that adequate pressure and volume of air is provided for fuel atomization during start-up of the engine. Further, the system is arranged so that the service compressor automatically assumes the load as its speed increases during the acceleration of the gas turbine engine. The system is designed so that the starting compressor will not be overloaded and can be completely isolated from the circuit if desired.
Inventors
- 👤 Willis Earl Rose
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 05:29
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/22; F02C7/236; F02C7/2365
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
186 words
A system for supplying compressed air providing atomized fuel to the fuel nozzles in gas turbine engines that include a compressor and a combustor, said system comprising: a starting compressor having an inlet and an outlet; constant speed drive means for driving said starting compressor; a service compressor having an inlet and an outlet and arranged to be driven by said engine; first conduit means connecting the outlet of said starting compressor in fluid communication with the inlet of said service compressor; second conduit means connecting the inlet of said starting compressor in fluid communication with said first conduit means and with the gas turbine compressor; one-way valve means located in said second conduit means permitting flow through said second conduit means from the inlet of said starting compressor and from the turbine compressor to said first conduit means and preventing flow in the opposite direction; and, third conduit means for connecting the outlet of said service compressor to the fuel nozzles, whereby said starting compressor provides compressed air to the nozzles during start-up and augments said service compressor until said service compressor reaches operating speed.
Claim 2
Independent Claim
186 words
A system for supplying compressed air providing atomized fuel to the fuel nozzles in gas turbine engines that include a compressor and a combustor, said system comprising: a starting compressor having an inlet and an outlet; constant speed drive means for driving said starting compressor; a service compressor having an inlet and an outlet and arranged to be driven by said engine; first conduit means connecting the outlet of said starting compressor in fluid communication with the inlet of said service compressor; second conduit means connecting the inlet of said starting compressor in fluid communication with said first conduit means and with the gas turbine compressor; one-way valve means located in said second conduit means permitting flow through said second conduit means from the inlet of said starting compressor and from the turbine compressor to said first conduit means and preventing flow in the opposite direction; and, third conduit means for connecting the outlet of said service compressor to the fuel nozzles, whereby said starting compressor provides compressed air to the nozzles during start-up and augments said service compressor until said service compressor reaches operating speed.
Claim 3
Dependent Claim
23 words
The system of claim 1 and also including valve means for isolating said starting compressor after said service compressor has reached operational speed.
Claim 4
Dependent Claim
43 words
The system of claim 1 and also including heat exchanger means located in said second conduit means between the gas turbine compressor and the inlet of said starting compressor for reducing the temperature of air flowing from the compressor to said starting compressor.
Claim 5
Dependent Claim
82 words
The system of claim 1 and also including: fourth conduit means connecting said first conduit means and third conduit means in fluid communication; and, second one-way valve means located in said fourth conduit means permitting flow from said first conduit means to said third conduit means and preventing flow in the opposite direction, whereby air can flow directly from said starting compressor to the fuel nozzles, bypassing said service compressor, in the event air does not flow easily through said service compressor.
Claim 6
Dependent Claim
22 words
The system of claim 4 and also including valve means for isolating said starting compressor after said service compressor reaches operational speed.
Claim 7
Dependent Claim
43 words
The system of claim 1 and also including heat exchanger means located in said second conduit means between the gas turbine compressor and the inlet of said starting compressor for reducing the temperature of air flowing from the compressor to said starting compressor.
References Cited (Backward Citations)
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US2813231A
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US2976683A
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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) | 1979-07-27 | 1980-01-26 | 1980-07-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-07-27 | 1984-01-26 | 1984-07-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-07-27 | 1988-01-26 | 1988-07-27 | $7700.00 | Window Closed / Lapsed |