US3878677A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Auxiliary turbine/compressor system for turbine engine
Assignee: RTX Corp
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Filing: 1974-04-10
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Granted: 1975-04-22
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Expires: 1994-04-10
Abstract
Abstract A gas turbine engine has incorporated therein an auxiliary turbine/compressor system providing for engine starting and providing compressed air for accessories during engine operation. A turbine/compressor unit is connected to the engine compressor for rotation therewith. For starting, compressed air is passed over the turbine/compressor unit utilizing it as a turbine, which thereby turns the compressor for starting while the air passing through the turbine/compressor unit then flows over the blades of the compressor into the burner. After starting, the compressor rotates the turbine/compressor unit and acting as a compressor it compresses ambient air and makes it available for use in driving air driven accessories. A valving system is provided to permit proper control of airflow. Variable position vanes are located at both ends of the turbine/compressor unit to control direction of airflow into and away from the unit as it is used as a turbine or compressor.
Inventors
- 👤 Donald C Colvin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 13:50
CPC Classifications
F; F02; F02C; F02C6/00; F02C6/04; F02C6/06; F02C6/08; F02C7/00; F02C7/26; F02C7/268; F02C7/275; F02C7/277; Y; Y10; Y10S; Y10S415/00; Y10S415/91
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
229 words
In combination a jet engine having compressor means, burner means, and turbine means, said compressor means having a compressor rotor with blades and a turbine/compressor unit connected thereto, said turbine/compressor unit having a rotor mounted for rotation with said rotor of said compressor means, said turbine/compressor unit rotor having blades therearound, shroud means covering the edges of the blades forming a passageway means for fluid flow through the blades of the rotor, said turbine/compressor unit having first opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, said turbine/compressor unit having a second opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, a first chamber having a connection with said first opening means, a second chamber having a connection with said second opening means, means for operating said turbine/compressor unit as a turbine comprising means for directing a compressed fluid to said first chamber for entry into said first opening means, said second chamber having third opening means for directing the fluid therein to the blades on said compressor rotor for entry into the burner, means for operating said turbine/compressor unit as a compressor comprising means for connecting said second chamber to a source of fluid, said first chamber having fourth opening means for directing the fluid therein to a device dependent on the compressed air.
Claim 2
Dependent Claim
229 words
In combination a jet engine having compressor means, burner means, and turbine means, said compressor means having a compressor rotor with blades and a turbine/compressor unit connected thereto, said turbine/compressor unit having a rotor mounted for rotation with said rotor of said compressor means, said turbine/compressor unit rotor having blades therearound, shroud means covering the edges of the blades forming a passageway means for fluid flow through the blades of the rotor, said turbine/compressor unit having first opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, said turbine/compressor unit having a second opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, a first chamber having a connection with said first opening means, a second chamber having a connection with said second opening means, means for operating said turbine/compressor unit as a turbine comprising means for directing a compressed fluid to said first chamber for entry into said first opening means, said second chamber having third opening means for directing the fluid therein to the blades on said compressor rotor for entry into the burner, means for operating said turbine/compressor unit as a compressor comprising means for connecting said second chamber to a source of fluid, said first chamber having fourth opening means for directing the fluid therein to a device dependent on the compressed air.
Claim 3
Dependent Claim
229 words
In combination a jet engine having compressor means, burner means, and turbine means, said compressor means having a compressor rotor with blades and a turbine/compressor unit connected thereto, said turbine/compressor unit having a rotor mounted for rotation with said rotor of said compressor means, said turbine/compressor unit rotor having blades therearound, shroud means covering the edges of the blades forming a passageway means for fluid flow through the blades of the rotor, said turbine/compressor unit having first opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, said turbine/compressor unit having a second opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, a first chamber having a connection with said first opening means, a second chamber having a connection with said second opening means, means for operating said turbine/compressor unit as a turbine comprising means for directing a compressed fluid to said first chamber for entry into said first opening means, said second chamber having third opening means for directing the fluid therein to the blades on said compressor rotor for entry into the burner, means for operating said turbine/compressor unit as a compressor comprising means for connecting said second chamber to a source of fluid, said first chamber having fourth opening means for directing the fluid therein to a device dependent on the compressed air.
Claim 4
Dependent Claim
229 words
In combination a jet engine having compressor means, burner means, and turbine means, said compressor means having a compressor rotor with blades and a turbine/compressor unit connected thereto, said turbine/compressor unit having a rotor mounted for rotation with said rotor of said compressor means, said turbine/compressor unit rotor having blades therearound, shroud means covering the edges of the blades forming a passageway means for fluid flow through the blades of the rotor, said turbine/compressor unit having first opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, said turbine/compressor unit having a second opening means for permitting fluid into or out of said passageway means of the turbine/compressor unit, a first chamber having a connection with said first opening means, a second chamber having a connection with said second opening means, means for operating said turbine/compressor unit as a turbine comprising means for directing a compressed fluid to said first chamber for entry into said first opening means, said second chamber having third opening means for directing the fluid therein to the blades on said compressor rotor for entry into the burner, means for operating said turbine/compressor unit as a compressor comprising means for connecting said second chamber to a source of fluid, said first chamber having fourth opening means for directing the fluid therein to a device dependent on the compressed air.
Claim 5
Dependent Claim
25 words
A combination as set forth in claim 1 wherein said first opening means and second opening means have variable vanes therein to control airflow thereby.
Claim 6
Dependent Claim
109 words
A combination as set forth in claim 1 wherein a third chamber is connected to said second chamber, said first and third chambers being connected to an annular manifold around said engine, said annular manifold being divided into two annular sections, one of said annular sections being connected to said first chamber while the other section is connected to said third chamber, said means for directing a compressed fluid to said first chamber being connected to said annular section of said manifold connected to said first chamber, said means for connecting said second chamber to a source of fluid being connected to the other annular section of said manifold.
Claim 7
Dependent Claim
29 words
A combination as set forth in claim 1 wherein said compressor means includes a low pressure compressor and a high pressure compressor, said rotor being located between said compressors.
Claim 8
Dependent Claim
18 words
A combination as set forth in claim 4 wherein said rotor is connected to said high pressure compressor.
References Cited (Backward Citations)
US2318905A
Cited
US2608054A
Cited
US2671635A
Cited
US2692476A
Cited
US2874540A
Cited
US3107489A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-04-21 | 1978-10-21 | 1979-04-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-04-21 | 1982-10-21 | 1983-04-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-04-21 | 1986-10-21 | 1987-04-22 | $7700.00 | Window Closed / Lapsed |