Patent US4182117A successfully refreshed from Google Patents.
US4182117A
Expired / Lapsed
US
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Diffuser vane cusp bleed aperture with automatic ejector control device
Assignee: Honeywell International Inc
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Filing: 1978-01-09
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Granted: 1980-01-08
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Expires: 1998-01-09
Abstract
Abstract In a gas turbine engine an auxiliary airflow is provided to power accessories. This auxiliary airflow is obtained from a bleed aperture which is constructed immediately downstream of a diffuser vane in a cusp which is formed in the trailing edge of the vane to provide inertial separation. This high energy air from the diffuser is used as the primary airflow in an ejector to draw ambient air into the auxiliary airflow to lower the temperature of the bleed air. The ejector is constructed to automatically adjust the amount of ambient air according to the energy of the bleed airflow by means of a piston actuated spike mounted for sliding movement in the primary nozzle. The spike varies the volume of flow through the primary nozzle according to the pressure exerted by the airflow on the piston.
Inventors
- 👤 John T. Exley
- 👤 Charles Kuintzle
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 16:05
CPC Classifications
F; F02; F02C; F02C6/00; F02C6/04; F02C6/06; F02C6/08; F04; F04D; F04D27/00; F04D27/02; F04D27/0207; F04D27/0215; F04D27/023; F04D29/00; F04D29/40; F04D29/42; F04D29/44; F04D29/441; F04D29/444; F05; F05D; F05D2250/00; F05D2250/50; F05D2250/52
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
84 words
In a gas turbine engine having a compressor stage which drives high energy airflow through a diffuser, means to bleed air from the diffuser comprising: a plurality of diffuser vanes mounted in the diffuser and having a curved cusp-like surface formed in the trailing edge thereof; a connecting duct constructed in the diffuser and communicating with the region within the cusp formed in the downstream end of the diffuser vane; and a bleed air manifold constructed to receive bleed air from the connecting duct.
Claim 2
Dependent Claim
84 words
In a gas turbine engine having a compressor stage which drives high energy airflow through a diffuser, means to bleed air from the diffuser comprising: a plurality of diffuser vanes mounted in the diffuser and having a curved cusp-like surface formed in the trailing edge thereof; a connecting duct constructed in the diffuser and communicating with the region within the cusp formed in the downstream end of the diffuser vane; and a bleed air manifold constructed to receive bleed air from the connecting duct.
Claim 3
Dependent Claim
94 words
In a gas turbine engine means to bleed air from the diffuser as described in claim 1, further comprising an ejector assembly having a primary and a secondary nozzle, said assembly being connected to the bleed air manifold so that the bleed air flows through the primary nozzle, said nozzle being constructed with means to automatically adjust the volumn of airflow in the primary nozzle inversely proportional to the energy of the airflow in the diffuser, said ejector assembly connected to draw cooling air through the secondary nozzle to combine with the bleed airflow.
Claim 4
Dependent Claim
147 words
In a gas turbine engine means to obtain bleed air from the diffuser as described in claim 2 wherein the means to vary the airflow in the primary nozzle of the ejector comprises: an elongated spike mounted for axial sliding motion within the primary nozzle and shaped so that this motion tends to vary the amount of airflow in the primary nozzle; a sealed chamber constructed within the ejector; a piston fixed to the nozzle spike for movement therewith and extending into the sealed chamber; a biasing spring operatively associated with the piston to bias the piston and spike in a position for maximum primary airflow; and means to expose one side of the piston to a force proportional to the pressure of the bleed air in the bleed manifold so that increased pressure will cause movement of the piston and spike to reduce the primary airflow.
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) | 1983-01-07 | 1983-07-09 | 1984-01-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1987-01-07 | 1987-07-09 | 1988-01-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1991-01-07 | 1991-07-09 | 1992-01-08 | $7700.00 | Window Closed / Lapsed |