Patent US3854286A successfully refreshed from Google Patents.
US3854286A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Variable bypass engines
Assignee: Boeing Co
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Filing: 1973-02-05
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Granted: 1974-12-17
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Expires: 1993-02-05
Abstract
Abstract Air breathing gas turbine engine design concepts, methods and apparatus for providing variable bypass and variable engine cycles. The disclosed preferred embodiments involve flow control systems for internal management of air within the engine which have a capability to crossover or invert adjacent annular flow patterns without interference, necking down, or departure from the confines of an annular passageway, and which may be switched from inverted to straight through flow.
Inventors
- 👤 G Klees
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 14:00
CPC Classifications
F; F02; F02K; F02K3/00; F02K3/08; F02K3/105; F02K3/02; F02K3/025; F02K3/04; F02K3/075; F02K3/077; F02K7/00; F02K7/10; F02K7/16; F05; F05D; F05D2220/00; F05D2220/80
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
125 words
A turbine engine having a centrally located housing containing a core gas generator, and a fluid flow control system located between a forward blade element and an aft blade element of said engine; said flow control system comprising means for inverting the respective positions of two separate adjacent annular flow patterns between the entrance and exit ends of said system, means for switching the respective positions of said two flow patterns from their inverted positions to the same respective positions at each of said entrance and exit ends; and wherein there is additionally included in said engine a core passageway means for supplying Intake air to said core gas generator which provides a flow path not affected by flow in said two separate flow patterns.
Claim 2
Dependent Claim
125 words
A turbine engine having a centrally located housing containing a core gas generator, and a fluid flow control system located between a forward blade element and an aft blade element of said engine; said flow control system comprising means for inverting the respective positions of two separate adjacent annular flow patterns between the entrance and exit ends of said system, means for switching the respective positions of said two flow patterns from their inverted positions to the same respective positions at each of said entrance and exit ends; and wherein there is additionally included in said engine a core passageway means for supplying Intake air to said core gas generator which provides a flow path not affected by flow in said two separate flow patterns.
Claim 3
Dependent Claim
26 words
The engine of claim 1 wherein the intake air supplied to said core gas generator has been compressed by at least one of said blade elements.
Claim 4
Dependent Claim
50 words
The engine of claim 2 wherein said two separate adjacent annular flow patterns are contained within an annular space having a cross-sectional area substantially equal to the total combined area of said two adjacent flow patterns at any longitudinal location between said entrance and said exit ends of said system.
Claim 5
Dependent Claim
32 words
The engine of claim 3 wherein said two separate adjacent annular flow patterns have substantially equal cross-sectional areas at any longitudinal location between said entrance and said exit ends of said system.
Claim 6
Dependent Claim
49 words
The engine of claim 3 wherein in a high bypass ratio mode of operation said forward blade element compresses fluid entering the innermost of said adjacent annular flow patterns, and the fluid thereby compressed is discharged at said exit end in an annular pattern surrounding said aft blade element.
Claim 7
Dependent Claim
53 words
The engine of claim 5 wherein in a low bypass ratio mode of operation said forward blade element compresses fluid entering the innermost of said adjacent annular flow pattern and the fluid thereby compressed is discharged at said exit end into the path of the aft blade element where it is again compressed.
Claim 8
Dependent Claim
32 words
The engine of claim 4 wherein said core passageway means occupies an annular region between said centrally located housing and said annular space occupied by said two separate adjacent annular flow patterns.
Claim 9
Dependent Claim
24 words
The engine of claim 7 wherein the intake air supplied to said core gas generator has been compressed by each of said blade elements.
Claim 10
Independent Claim
177 words
A method for improving the efficiency of a propulsion engine having an annular passageway for control of propulsive fluid, said method comprising: dividing said passageway into first, second, and third annular flow patterns such that said first flow pattern is located adjacent to, inside of, and concentric with, said second flow pattern at the entrance end of said passageway and said third flow pattern is located adjacent to, inside of, and concentric with said first flow pattern at the entrance end of said passageway; compressing the fluid flowing into the first flow pattern; discharging said first and second flow patterns at the exit end of said passageway in an inverted spatial relationship to that which exists at the entrance end of said passageway such that said second flow pattern is located adjacent to, inside of, and concentric with, said first flow pattern; directing fluid in said third flow pattern into the core gas generator of said engine; and directing fluid flowing out of said passageway into an annular bypass duct for delivery to a discharge nozzle system.
Claim 11
Independent Claim
177 words
A method for improving the efficiency of a propulsion engine having an annular passageway for control of propulsive fluid, said method comprising: dividing said passageway into first, second, and third annular flow patterns such that said first flow pattern is located adjacent to, inside of, and concentric with, said second flow pattern at the entrance end of said passageway and said third flow pattern is located adjacent to, inside of, and concentric with said first flow pattern at the entrance end of said passageway; compressing the fluid flowing into the first flow pattern; discharging said first and second flow patterns at the exit end of said passageway in an inverted spatial relationship to that which exists at the entrance end of said passageway such that said second flow pattern is located adjacent to, inside of, and concentric with, said first flow pattern; directing fluid in said third flow pattern into the core gas generator of said engine; and directing fluid flowing out of said passageway into an annular bypass duct for delivery to a discharge nozzle system.
Claim 12
Dependent Claim
52 words
The method of claim 9 which further includes: selectively changing the bypass ratio of said engine by switching the relative positions of said first and second flow patterns at the exit end of said passageway such that said first flow pattern remains located inside of and concentric with said second flow pattern.
Claim 13
Dependent Claim
36 words
The method of claim 9 which further includes maintaining the fluid in said third flow pattern at a pressure which is independent of the pressures existing in the fluid of said first and second flow patterns.
Claim 14
Dependent Claim
148 words
A gas turbine engine including compressor, burner and turbine means; a first fan driven by said turbine means; a first annular wall in the path of flow from said first fan whereby the first fan flow is divided into first and second concentric annuli; a second annular wall surrounding said first fan; a third annular wall of greater diameter than said second annular wall and defining therewith a third annulus; a second fan axially spaced from said first fan; and valve means interposed between said first and second fans defining passageways which, in a first valve position, connect Said second annulus to said aft fan, whereby said first and second fans are in series, and in a second valve position defining passageways between said third annulus and said second fan and from said second annulus bypassing said second fan, whereby the first and second fans are in parallel.
Claim 15
Dependent Claim
148 words
A gas turbine engine including compressor, burner and turbine means; a first fan driven by said turbine means; a first annular wall in the path of flow from said first fan whereby the first fan flow is divided into first and second concentric annuli; a second annular wall surrounding said first fan; a third annular wall of greater diameter than said second annular wall and defining therewith a third annulus; a second fan axially spaced from said first fan; and valve means interposed between said first and second fans defining passageways which, in a first valve position, connect Said second annulus to said aft fan, whereby said first and second fans are in series, and in a second valve position defining passageways between said third annulus and said second fan and from said second annulus bypassing said second fan, whereby the first and second fans are in parallel.
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) | 1977-12-16 | 1978-06-17 | 1978-12-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-12-16 | 1982-06-17 | 1982-12-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-12-16 | 1986-06-17 | 1986-12-17 | $7700.00 | Window Closed / Lapsed |