Patent US3604629A successfully refreshed from Google Patents.
US3604629A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Thrust reversing mechanism
Assignee: Rolls Royce PLC
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Filing: 1970-01-05
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Granted: 1971-09-14
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Expires: 1990-01-05
Abstract
Abstract A ducted fan gas turbine jet propulsion engine has thrust reverser equipment in the fan cowl structure. Blocker doors or flaps are mounted peripherally of the fan cowl inner wall, and between adjacent blocker flaps there are fillet flaps also mounted so as to provide an uninterrupted surface in the fan cowl inner wall. The fillet flaps are pivotable on an axis generally parallel to the axis of the engine so that when the flaps are pivoted they lie edge on to fan air flowing through the reverser equipment. Each fillet flap has at least one side aerodynamically shaped so as to create a pressure differential on opposite sides thereof when the blocker flaps are in blocking position, and thus reduce or prevent ''''positional hunting'''' of the fillet flaps in the airflow.
Inventors
- 👤 Francis J Colville
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 12:34
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/54; F02K1/64; F02K1/70; F02K1/72
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
122 words
A thrust reverser for controlling the flow of fluid through an aperture in a cowl structure defining a wall of a fan duct of a ducted fan-type of gas turbine jet propulsion engine, the thrust reverser comprising at least one flap member mounted within the aperture and movable from a first position wherein it at least partly obturates the aperture, to a second position wherein both sides of the flap member are exposed to the flow of fluid therethrough and are parallel therewith, said flap member having a configuration for imparting to fluid flowing past one side thereof, flow characteristics different from the flow characteristics of the fluid flowing past the other side thereof so as to create a pressure differential therebetween.
Claim 2
Dependent Claim
122 words
A thrust reverser for controlling the flow of fluid through an aperture in a cowl structure defining a wall of a fan duct of a ducted fan-type of gas turbine jet propulsion engine, the thrust reverser comprising at least one flap member mounted within the aperture and movable from a first position wherein it at least partly obturates the aperture, to a second position wherein both sides of the flap member are exposed to the flow of fluid therethrough and are parallel therewith, said flap member having a configuration for imparting to fluid flowing past one side thereof, flow characteristics different from the flow characteristics of the fluid flowing past the other side thereof so as to create a pressure differential therebetween.
Claim 3
Dependent Claim
32 words
A thrust reverser as claimed in claim 1 wherein the at least one side of the at least one flap member has at least a portion thereof formed into an airfoil shape.
Claim 4
Dependent Claim
22 words
A thrust reverser as claimed in claim 1 wherein the at least one flap member is spring urged into its obturating position.
Claim 5
Dependent Claim
39 words
A thrust reverser as claimed in claim 2 wherein the flap member is mounted for pivotal movement to the second position whereby to present the leading edge of said airfoil shape to the flow of fluid through the aperture.
Claim 6
Dependent Claim
28 words
A thrust reverser as claimed in claim 1 wherein the at least one flap member comprises part of the outer wAll of the fan duct of said engine.
Claim 7
Dependent Claim
37 words
A thrust reverser as claimed in claim 5 wherein a plurality of said flap members are arranged in pairs circumferentially of said cowl structure and each pair being alternately spaced in relationship with further blocker flap members.
Claim 8
Dependent Claim
33 words
A thrust reverser claimed in claim 6 wherein said further blocker flap members are adapted to selectively block off the fan duct so as to prevent fluid flowing through the duct axially thereof.
Claim 9
Dependent Claim
28 words
A thrust reverser as claimed in claim 1 wherein said cowl structure has a portion movable axially of the fan duct between positions covering and opening said aperture.
Claim 10
Dependent Claim
55 words
A valve as claimed in claim 8 wherein the flap members, aperture and movable cowl portion are aligned radially of the engine axis. l0. A valve as claimed in claim 9 wherein guide vanes are provided in said aperture between said cowl portion and said flap members whereby to guide or deflect fluid flowing therethrough.
Claim 11
Dependent Claim
150 words
In a gas turbine jet propulsion engine of the ducted fan-type: a fan cowl structure surrounding a casing of said engine and defining therewith a fan duct, said fan cowl structure having an aperture therethrough; a thrust reverser mechanism for deflecting fan duct fluid through said aperture in said fan cowl structure from its normal flow path, said thrust reverser mechanism comprising a plurality of circumferentially spaced blocker flaps movable between a position partially obturating the aperture of said cowl structure and a position blocking off the fan duct and deflecting the fluid through the aperture, fillet flap means carried by said cowl structure intermediate adjacent blocker flaps when said blocker flaps are partially obturating the aperture to thereby completely obturate the aperture, said fillet flap means being operated to an open position under pressure from deflected fluid when said blocker flaps are in position to block the fan duct.
Claim 12
Dependent Claim
150 words
In a gas turbine jet propulsion engine of the ducted fan-type: a fan cowl structure surrounding a casing of said engine and defining therewith a fan duct, said fan cowl structure having an aperture therethrough; a thrust reverser mechanism for deflecting fan duct fluid through said aperture in said fan cowl structure from its normal flow path, said thrust reverser mechanism comprising a plurality of circumferentially spaced blocker flaps movable between a position partially obturating the aperture of said cowl structure and a position blocking off the fan duct and deflecting the fluid through the aperture, fillet flap means carried by said cowl structure intermediate adjacent blocker flaps when said blocker flaps are partially obturating the aperture to thereby completely obturate the aperture, said fillet flap means being operated to an open position under pressure from deflected fluid when said blocker flaps are in position to block the fan duct.
Claim 13
Dependent Claim
37 words
A gas turbine jet propulsion engine as claimed in claim 11, in which each fillet flap means includes a pair of flap members arranged to pivot on an axis generally parallel to the axis of the engine.
Claim 14
Dependent Claim
27 words
A gas turbine jet propulsion engine as claimed in claim 12, including resilient means normally urging said fillet flap members to their position partially obturating the aperture.
Claim 15
Dependent Claim
57 words
A gas turbine jet propulsion engine as claimed in claim 12, in which said fillet flap members have an airfoil configuration on at least one side thereof so as to create a pressure differential thereon and prevent hunting when said fillet flap members are pivoted to an unobturating position by pressure of fluid flowing through the aperture.
References Cited (Backward Citations)
US3262270A
Cited
US3497165A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-09-13 | 1975-03-15 | 1975-09-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-09-13 | 1979-03-15 | 1979-09-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-09-13 | 1983-03-15 | 1983-09-14 | $7700.00 | Window Closed / Lapsed |