US3905191A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine with efficient annular bleed manifold
Assignee: Avco Corp
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Filing: 1974-04-10
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Granted: 1975-09-16
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Expires: 1994-04-10
Abstract
Abstract A gas turbine engine has an annular bleed manifold for cabin pressurization and other purposes. The bleed manifold is positioned at a point intermediate the ends of the engine combustor to utilize the highest available engine pressure for these purposes. A deflector in the form of a continuous band or a series of chutes permits entry of air through openings into the manifold but deflects particulate matter away from the opening thereby insuring clean cabin pressurization air.
Inventors
- 👤 Lawrence R Matto
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 11:00
CPC Classifications
F; F04; F04D; F04D29/00; F04D29/40; F04D29/42; F04D29/44; F04D29/441; F04D27/00; F04D27/02; F04D27/0207; F04D27/023
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
178 words
A gas turbine engine comprising: an annular outer housing; a driven compressor journaled within said housing for pressurizing ambient air; a combustor positioned within said housing downstream from said compressor and receiving the pressurized air therefrom; means for injecting fuel into said combustor for producing a combustible mixture ignitable to produce a propulsive gas stream; an annular bleed chamber positioned at said combustor around at least a portion of the periphery of said housing at a position experiencing the maximum pressure for air discharged from said compressor, said housing having openings connecting the interior of said housing to said annular bleed chamber, said annular bleed chamber is defined by a channel-shaped element extending around the periphery of said housing and terminating in ends defining a gap adjacent the bottom of said housing and said housing is imperforate in the area of said gap, thereby minimizing entry of raw fuel into said manifold; and deflector means positioned over said openings so as to permit entry of air into said bleed chamber but deflect particulate matter away from said openings.
Claim 2
Dependent Claim
178 words
A gas turbine engine comprising: an annular outer housing; a driven compressor journaled within said housing for pressurizing ambient air; a combustor positioned within said housing downstream from said compressor and receiving the pressurized air therefrom; means for injecting fuel into said combustor for producing a combustible mixture ignitable to produce a propulsive gas stream; an annular bleed chamber positioned at said combustor around at least a portion of the periphery of said housing at a position experiencing the maximum pressure for air discharged from said compressor, said housing having openings connecting the interior of said housing to said annular bleed chamber, said annular bleed chamber is defined by a channel-shaped element extending around the periphery of said housing and terminating in ends defining a gap adjacent the bottom of said housing and said housing is imperforate in the area of said gap, thereby minimizing entry of raw fuel into said manifold; and deflector means positioned over said openings so as to permit entry of air into said bleed chamber but deflect particulate matter away from said openings.
Claim 3
Dependent Claim
53 words
A gas turbine engine as in claim 1 wherein said deflector comprises a continuous band secured to said housing upstream of said holes and extending radially inward and in a Downstream direction a sufficient amount to project beyond the openings whereby air passing to said bleed chamber passes through an aft facing opening.
Claim 4
Dependent Claim
69 words
A gas turbine engine as in claim 1 wherein said deflector comprises a plurality of chutes secured to said housing around each of said holes, said chutes having a base secured to said housing and triangular-shaped side walls projecting inward and a wall extending between the side walls to a opening through which air must pass in an upstream direction before passing through said openings into said bleed chamber.
Claim 5
Dependent Claim
34 words
A gas turbine engine as in claim 1 further comprising a strap connected to the ends of said channel element and extending across said gap to resist hoop stresses imposed on said channel element.
Claim 6
Dependent Claim
29 words
A gas turbine engine as in claim 1 further comprising at least one distribution opening positioned in said channel element for connecting the air therein to a utilization device.
Claim 7
Dependent Claim
112 words
A gas turbine engine as in claim 1 wherein: said compressor includes centrifugal impeller directing air radially outward and a diffuser around the periphery of said centrifugal stage for increasing the static pressure of the air; said combustor is of the reverse flow type in which the head end of the combustor is positioned downstream with respect to the air flowing into the housing around said combustor and the downstream outlet of said combustor is positioned in the upstream end of said housing; said bleed chamber and said openings are positioned at a point intermediate the ends of said combustor thereby connecting with a point of maximum static pressure in said engine.
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) | 1978-09-15 | 1979-03-17 | 1979-09-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-15 | 1983-03-17 | 1983-09-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-15 | 1987-03-17 | 1987-09-16 | $7700.00 | Window Closed / Lapsed |