US3659418A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Variable gas turbine engine air intake
Assignee: Rolls Royce PLC
•
Filing: 1970-07-13
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Granted: 1972-05-02
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Expires: 1990-07-13
Abstract
Abstract A vortex air flow is set up around the outer fringe of an air flow through a duct, the internal diameter of which increases in a downstream direction. The vortex picks up the outer fringe of the air flow in the duct and causes it to diffuse more rapidly onto the increased diameter portion of the duct, than would normally occur.
Inventors
- 👤 Michael Poucher
- 👤 Michael Roy Williams
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 11:28
CPC Classifications
F; F01; F01D; F01D9/00; F02; F02C; F02C7/00; F02C7/04; F02C7/042; F23; F23R; F23R3/00; F23R3/02; Y; Y10; Y10S; Y10S415/00; Y10S415/914; Y10T; Y10T137/00; Y10T137/0536
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
214 words
A gas turbine engine comprising: an air intake, compressor means, combustion equipment and turbine means in flow series, said air intake having at least one diffusing fluid flow duct for flow of fluid therethrough and said duct comprising an upstream wall portion and a downstream diverging wall portion adapted to be spaced therefrom to define a discontinuity therebetween, said upstream wall portion and downstream diverging wall portion being formed by pairs of flap members, each pair of said flap members being adjacent axially of the duct with each other and hinged so as to be moveable to reduce said ducts width relative to its width downstream of the upstream wall portion and downstream diverging wall portion, means defining a toroidal cavity between said upstream wall portion and said downstream diverging wall portion, said toroidal cavity being adapted to be open to said discontinuity between said upstream wall portion and said downstream diverging wall portion, and means for promoting a fluid vortex in said toroidal cavity to define a variable shaped fluid wall across said discontinuity, said fluid vortex circulating in a direction to impinge upon and promote attachment of fluid flowing in said duct leaving the upstream wall portion onto the downstream wall portion without breakaway and turbulence along said downstream diverging wall portion.
Claim 2
Dependent Claim
214 words
A gas turbine engine comprising: an air intake, compressor means, combustion equipment and turbine means in flow series, said air intake having at least one diffusing fluid flow duct for flow of fluid therethrough and said duct comprising an upstream wall portion and a downstream diverging wall portion adapted to be spaced therefrom to define a discontinuity therebetween, said upstream wall portion and downstream diverging wall portion being formed by pairs of flap members, each pair of said flap members being adjacent axially of the duct with each other and hinged so as to be moveable to reduce said ducts width relative to its width downstream of the upstream wall portion and downstream diverging wall portion, means defining a toroidal cavity between said upstream wall portion and said downstream diverging wall portion, said toroidal cavity being adapted to be open to said discontinuity between said upstream wall portion and said downstream diverging wall portion, and means for promoting a fluid vortex in said toroidal cavity to define a variable shaped fluid wall across said discontinuity, said fluid vortex circulating in a direction to impinge upon and promote attachment of fluid flowing in said duct leaving the upstream wall portion onto the downstream wall portion without breakaway and turbulence along said downstream diverging wall portion.
Claim 3
Dependent Claim
41 words
A gas turbine engine as claimed in claim 1 wherein adjacent edges of each pair of flap members include sTructure defining a portion of said toroidal cavity when said flap members are moved to a position reducing width of said duct.
Claim 4
Dependent Claim
49 words
A gas turbine engine as claimed in claim 2 wherein the fluid flowing in said air intake has an angle of diffusion of its outer layers which is increased by impingement thereon of fluid from said fluid vortex when said flap members are moved to said width reducing position.
Claim 5
Dependent Claim
41 words
A gas turbine engine as claimed in claim 2 wherein said means for promoting the fluid vortex in said toroidal cavity includes an air tapping conduit extending from a source of compressed air and opening at least to said toroidal cavity.
Claim 6
Dependent Claim
37 words
A gas turbine engine as claimed in claim 4 including nozzle means also connected to said tapping conduit for directing some of the air along the downstream diverging wall portion to provide a moving wall there along.
Claim 7
Dependent Claim
36 words
A gas turbine engine as claimed in claim 2 including means to provide a moving fluid wall along said diverging downstream wall portion between the same and outer layers of the fluid flowing in said duct.
Claim 8
Dependent Claim
26 words
A gas turbine engine as claimed in claim 6 in which said last mentioned means includes nozzle means operatively connected to a source of compressed air.
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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) | 1975-05-02 | 1975-11-01 | 1976-05-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-05-02 | 1979-11-01 | 1980-05-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-05-02 | 1983-11-01 | 1984-05-02 | $7700.00 | Window Closed / Lapsed |