US3920203A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Thrust control apparatus for obtaining maximum thrust reversal in minimum time upon landing of an aircraft
Assignee: Boeing Co
•
Filing: 1974-12-23
•
Granted: 1975-11-18
•
Expires: 1994-12-23
Abstract
Abstract The thrust control apparatus of the present invention is employed on an aircraft having a wing and a turbofan engine mounted on a strut extending downwardly and forwardly from the wing. The thrust control apparatus includes (a) a rearwardly opening turbine engine nozzle for directing primary turbine exhaust effluent rearwardly from the engine, (b) a fan and an annular fan duct surrounding the forward portion of the turbine engine, (c) a primary fan air duct being coupled to the annular fan air duct, extending upwardly and rearwardly from the annular fan duct, and terminating in a separate rearwardly opening fan air nozzle for directing the secondary fan effluent rearwardly from the engine, and (d) a first auxiliary duct being coupled to the primary fan air duct, extending upwardly therefrom, and terminating in an upwardly opening auxiliary fan air nozzle for directing fan air flowing through the first auxiliary duct upwardly in front of the aircraft wing. During cruise operation, a valve associated with the coupling between the primary duct and the first auxiliary duct is positioned to close the first auxiliary duct, allowing all of the fan effluent to be exhausted through the fan air nozzle. Upon approach to landing, the valve associated with the coupling of the primary duct and the first auxiliary duct is adjusted to a position where it bifurcates the fan effluent between the primary duct and the first auxiliary duct. At the same time the engine throttle is advanced, calling for the turbofan engine to generate near maximum r.p.m. A plurality of vanes in the first auxiliary nozzle directs the fan effluent flowing through the first auxiliary duct upwardly and rearwardly over the upper airfoil surface of the wing. Upon touchdown of the aircraft on the landing field, the valve associated with the coupling between the primary duct and the first auxiliary duct closes the primary duct diverting the entire flow of fan effluent through the first auxiliary duct. At the same time the plurality of vanes in the first auxiliary nozzle are shifted to direct the fan effluent upwardly and forwardly relative to the engine and the wing, thus reversing the flow direction of the fan effluent and providing a reverse thrust component to brake the aircraft.
Inventors
- 👤 James R Moorehead
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 11:34
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/54; F02K1/64; F02K1/70; B; B64; B64C; B64C21/00; B64C21/02; B64C21/04; B64C2230/00; B64C2230/04; B64C2230/06; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 22
Claim 1
Independent Claim
391 words
Thrust control apparatus for a turbofan jet propulsion engine in combination with an aircraft wing and means mounting said engine on said wing, said turbofan jet propulsion engine including a turbine engine having an outer wall terminating in a turbine engine nozzle means for directing a primary exhaust effluent rearwardly from said turbine engine relative to said wing, a cowling surrounding and spaced outwardly from a portion of the wall of said turbine, said cowling and the wall of said turbine defining therebetween a rearwardly extending annular fan duct, and a fan driven by said turbine engine, said fan being operatively positioned in said duct to generate a secondary exhaust effluent and direct said secondary effluent rearwardly through said fan duct, said wing including an upper airfoil surface said apparatus comprising: a. a primary duct including means operatively coupling said primary duct to said fan duct for collecting said secondary effluent from said fan duct and including fan nozzle means for directing said secondary effluent rearwardly relative to said wing, b. an auxiliary duct including means operatively coupling said auxiliary duct to said primary duct and including auxiliary nozzle means for directing said secondary effluent flowing through said auxiliary duct in an upward direction relative to said wing, c. first valve means operatively associated with said primary duct and said auxiliary duct for varying the flow therethrough, said first valve means being selectively adjustable between 1. a cruise position wherein said first valve means is oriented to close said auxiliary duct and to permit flow of said secondary effluent through said primary duct, 2. at least one intermediate approach position wherein said first valve means is oriented in relation to said primary duct and said auxiliary duct to bifurcate the flow of said secondary effluent between said primary duct and said auxiliary duct, and 3. a reversing position wherein said first valve means is oriented to close said primary duct and to permit flow of said secondary effluent through said auxiliary duct, and d. vane means operatively associated with said auxiliary nozzle means, said vane means being selectively movable between 1. an approach position wherein said vane means is oriented to divert said secondary effluent rearwardly relative to said wing, and 2. a reversing position wherein said vane means is oriented to divert said secondary effluent forwardly relative to said wing.
Claim 2
Dependent Claim
391 words
Thrust control apparatus for a turbofan jet propulsion engine in combination with an aircraft wing and means mounting said engine on said wing, said turbofan jet propulsion engine including a turbine engine having an outer wall terminating in a turbine engine nozzle means for directing a primary exhaust effluent rearwardly from said turbine engine relative to said wing, a cowling surrounding and spaced outwardly from a portion of the wall of said turbine, said cowling and the wall of said turbine defining therebetween a rearwardly extending annular fan duct, and a fan driven by said turbine engine, said fan being operatively positioned in said duct to generate a secondary exhaust effluent and direct said secondary effluent rearwardly through said fan duct, said wing including an upper airfoil surface said apparatus comprising: a. a primary duct including means operatively coupling said primary duct to said fan duct for collecting said secondary effluent from said fan duct and including fan nozzle means for directing said secondary effluent rearwardly relative to said wing, b. an auxiliary duct including means operatively coupling said auxiliary duct to said primary duct and including auxiliary nozzle means for directing said secondary effluent flowing through said auxiliary duct in an upward direction relative to said wing, c. first valve means operatively associated with said primary duct and said auxiliary duct for varying the flow therethrough, said first valve means being selectively adjustable between 1. a cruise position wherein said first valve means is oriented to close said auxiliary duct and to permit flow of said secondary effluent through said primary duct, 2. at least one intermediate approach position wherein said first valve means is oriented in relation to said primary duct and said auxiliary duct to bifurcate the flow of said secondary effluent between said primary duct and said auxiliary duct, and 3. a reversing position wherein said first valve means is oriented to close said primary duct and to permit flow of said secondary effluent through said auxiliary duct, and d. vane means operatively associated with said auxiliary nozzle means, said vane means being selectively movable between 1. an approach position wherein said vane means is oriented to divert said secondary effluent rearwardly relative to said wing, and 2. a reversing position wherein said vane means is oriented to divert said secondary effluent forwardly relative to said wing.
Claim 3
Dependent Claim
40 words
at least one intermediate approach position wherein said first valve means is oriented in relation to said primary duct and said auxiliary duct to bifurcate the flow of said secondary effluent between said primary duct and said auxiliary duct, and
Claim 4
Dependent Claim
40 words
at least one intermediate approach position wherein said first valve means is oriented in relation to said primary duct and said auxiliary duct to bifurcate the flow of said secondary effluent between said primary duct and said auxiliary duct, and
Claim 5
Dependent Claim
19 words
a reversing position wherein said vane means is oriented to divert said secondary effluent forwardly relative to said wing.
Claim 6
Dependent Claim
19 words
a reversing position wherein said vane means is oriented to divert said secondary effluent forwardly relative to said wing.
Claim 7
Dependent Claim
82 words
The thrust control apparatus of claim 1 wherein said auxiliary nozzle means is located forwardly of said wing to direct said secondary effluent flowing through said auxiliary duct upwardly relative to said wing and in front of said wing, and wherein said vane means is located within said auxiliary nozzle means and is so oriented when in said approach position to divert said secondary effluent exhausting from said auxiliary nozzle means upwardly and rearwardly over the upper airfoil surface of said wing.
Claim 8
Dependent Claim
35 words
an approach position wherein said second valve means is oriented to stop the flow of secondary effluent from said fan nozzle means and to permit flow of said secondary effluent through said second auxiliary duct.
Claim 9
Dependent Claim
35 words
an approach position wherein said second valve means is oriented to stop the flow of secondary effluent from said fan nozzle means and to permit flow of said secondary effluent through said second auxiliary duct.
Claim 10
Dependent Claim
175 words
The thrust control apparatus of claim 2 wherein said wing further includes a trailing edge flap that is movable between a retracted position wherein said upper airfoil surface has a geometry suitable for high speed flight and an extended position increasing the camber of said wing wherein said upper airfoil surface has a geometry suitable for approach and take-off, said apparatus further comprising: a second auxiliary duct including means operatively coupling said second auxiliary duct to said primary duct at a location rearwardly from the location at which said first auxiliary duct is coupled to said primary duct, said second auxiliary duct further including auxiliary nozzle means associated with said wing and oriented to direct secondary effluent flowing through said second auxiliary duct in a rearward direction over at least the rearward portion of said upper airfoil surface of said wing including said trailing edge flap, and a second valve means operatively associated with said primary duct and said second auxiliary duct for varying the flow therethrough, said second valve means being selectively adjustable between
Claim 11
Dependent Claim
45 words
a reversing position wherein said first valve means is oriented to close said primary duct and to permit flow of said secondary effluent through said auxiliary duct, and d. vane means operatively associated with said auxiliary nozzle means, said vane means being selectively movable between
Claim 12
Dependent Claim
45 words
a reversing position wherein said first valve means is oriented to close said primary duct and to permit flow of said secondary effluent through said auxiliary duct, and d. vane means operatively associated with said auxiliary nozzle means, said vane means being selectively movable between
Claim 13
Dependent Claim
165 words
The thrust control apparatus of claim 3 wherein said wing has a leading edge, said wing further including a boundary layer control slot located adjacent the forward portion of said wing and oriented to direct effluent flowing therefrom rearwardly across the upper airfoil surface of said wing, said apparatus further comprising: a third auxiliary duct including means operatively coupling said third auxiliary duct to said primary duct at a location rearwardly from the location at which said first auxiliary duct is coupled to said primary duct and forwardly of the location at which said second auxiliary duct is coupled to said primary duct, said third auxiliary duct further including means operatively coupling said third auxiliary duct to said leading edge boundary layer control slot for channeling at least a portion of said secondary effluent from said primary duct to said leading edge boundary layer control slot, and third valve means operatively associated with said third auxiliary duct for opening and closing said third auxiliary duct.
Claim 14
Dependent Claim
53 words
The thrust control apparatus of claim 4 further comprising: nozzle thrust spoiler means operatively associated with said turbine engine nozzle means for selectively varying the effective outlet area of said turbine engine nozzle means to vary the forward thrust derived from said primary effluent being rearwardly discharged from said turbine engine nozzle means.
Claim 15
Dependent Claim
92 words
The thrust control apparatus of claim 5 wherein said means mounting said engine on said wing comprises a strut having an upper end and a lower end, the upper end of said strut being affixed to the lower portion of said wing, said strut extending downwardly and forwardly from said wing, the lower end of said strut being fixed to said jet propulsion engine to positin said jet propulsion engine below said wing and to position a major portion of said jet propulsion engine forwardly of the forward portion of said wing.
Claim 16
Dependent Claim
204 words
The thrust control apparatus of claim 6 wherein means coupling said primary duct to said fan duct includes a forward collector portion and a central collector portion, said forward collector portion being coupled to said annular fan duct to receive secondary effluent flowing therethrough, said forward collector portion being annularly shaped and surrounding the wall of said turbine, said central collector portion being coupled to said forward collector portion, said primary duct further including a rearwardly extending circularly shaped duct portion positioned above said turbine nozzle, said fan nozzle means being operatively coupled to said circularly shaped duct portion, said central collector portion extending upwardly and rearwardly from said forward collector portion about the wall of said turbine engine and being coupled to and merging into said rearwardly extending, circularly shaped duct portion, at least the forward collector portion of said primary duct being affixed to and supported by said strut, and wherein said strut has a generally upwardly and forwardly facing portion located Forwardly and below the forward portion of said wing, said first auxiliary duct being located within said strut, said first nozzle means associated with said first auxiliary duct being located in said upwardly and forwardly facing portion of said strut.
Claim 17
Dependent Claim
272 words
The thrust control apparatus of claim 7 wherein the central collector portion of said primary duct has an upper wall and wherein the means coupling said first auxiliary duct to said primary duct is positioned above and coupled to the central collector portion of said primary duct, the junction of said first auxiliary duct and said primary duct being a first auxiliary opening in the upper wall of the central collector portion of said primary duct, said first auxiliary opening having an aft end, said first valve means comprising a door member and means mounting said door member for fore and aft swinging movement relative to said wing at a location adjacent the aft end of said first auxiliary opening, said door member being sized such that, a. when said door member is moved to said reversing position, said door member swings downwardly to a position closing said primary duct to flow of secondary effluent and diverting the entire flow of secondary secondary into said first auxiliary duct, b. when said door member is moved to said cruise position said first auxiliary opening is closed to stop the flow of said secondary effluent through said auxiliary duct and to permit flow of said secondary effluent through said primary duct, and c. when said door member is moved to one of said intermediate positions between said cruise position and said approach position, said door member swings to an intermediate location in said primary duct to open said first auxiliary opening in said primary duct and to divert a portion of said secondary effluent flowing through said primary duct into said first auxiliary duct.
Claim 18
Dependent Claim
118 words
The thrust control apparatus of claim 8 wherein said door member can be positioned in a plurality of intermediate positions said door member in one of said intermediate positions being oriented in said primary duct such that substantially no load is placed upon said door member by said secondary effluent flowing through said primary duct while a portion of said secondary effluent is being bifurcated and diverted by said door member into said first auxiliary duct, said door member in the other of said intermediate positions being oriented to divert a lesser portion of said secondary effluent into said first auxiliary duct while permitting a greater proportion of said secondary effluent to flow through said first auxiliary duct.
Claim 19
Dependent Claim
188 words
The thrust control apparatus of claim 1 further comprising: first actuating means for selectively positioning said vane means in said approach position and in said reversing position, second actuating means for selectively positioning said first valve means in said cruise position, in said at least one intermediate position, and in said reversing position, initiation means for providing a first signal and means for transmitting said first signal to said first and second actuating means, said first actuating means being responsive to said first signal to position said vane means in said approach positions, and said second actuating means being responsive to said first signal to position said first valve means in said at least one intermediate position, and touchdown sensing means for generating a second signal when said aircraft contacts the ground upon landing and means for transmitting said second signal to said first and second actuating means, said first actuating means being responsive to said second signal to position said vane means in said reversing position, and said second actuating means being responsive to said second signal to position said first valve means in said reversing position.
Claim 20
Dependent Claim
214 words
The thrust control apparatus of claim 1 wherein said turbofan jet propulsion engine has a throttle for varying the thrust generated by said engine, said apparatus further comprising: first actuating means for selectively positioning said vane means in said approach position and in said reversing position, second actuating means for selectively positioning said first valve means in said cruise position, in said at least one intermediate position, and in said reversing position, engine throttle actuating means for varying the throttle setting of said turbofan jet propulsion engine between at least a first intermediate setting wherein said engine is generating less than maximum thrust and a second throttle setting wherein said engine is generating greater thrust than when said throttle is at said intermediate setting, initiation means for providing a first signal and means for transmitting said first signal to said first and second actuating means and to said engine throttle actuating means, said first actuating means being responsive to said first signal to position said vane means in said approach position, said second actuating means being responsive to said first signal to position said first valve means in said at least one intermediate position, said throttle actuating means being responsive to said first signal to advance said engine throttle to said second throttle setting.
Claim 21
Dependent Claim
319 words
The thrust control apparatus of claim 1 further comprising: nozzle thrust spoiler means being so constructed and operatively associated with said turbine engine nozzle means for selectively varying the effective outlet area of said turbine engine nozzle means to vary the forward thrust derived from said primary effluent being rearwardly discharged from said turbine engine nozzle means, first actuating means for selectively positioning said vane means in said approach position and in said reversing position, second actuating means for selectively positioning said first valve means in said cruise position, in said at least one intermediate position, and in said reversing position, nozzle spoiler actuating means for selectively positioning said nozzle thrust spoiler means between at least a first position wherein the effective outlet area is maximized to minimize the thrust derived from said primary effluent and at least a second position wherein said outlet area is reduced relative to the outlet area when in said first position to increase the thrust derived from said primary effluent, initiation means for providing a first signal and means for transmitting said first signal to said first and second actuating means, said first actuating means being responsive to said first signal to position said vane means in said approach position, said second actuating means being responsive to said first signal position said first valve means in said at least one intermediate position, said nozzle thrust spoiler actuating means being responsive to said first signal to position said nozzle thrust spoiler means in said first position, and touchdown sensing means for generating a second signal when said aircraft contacts the ground and means for transmitting said second signal to said first and second actuating means, said first actuating means being responsive to said second signal to position said vane means in said reversing position, said second actuating means being responsive to said second signal to position said first valve means in said reversing position.
Claim 22
Dependent Claim
81 words
The thrust control apparatus of claim 12 further comprising: manual actuating means operatively coupled to said nozzle spoiler actuating means to selectively vary the position of said nozzle thrust spoiler means between said first and second positions to very the thrust derived from said primary effluent, said nozzle spoiler actuating means being further responsive to said second signal to override said manual actuating means and to position said thrust spoiler means in said first position when said aircraft contacts the ground.
References Cited (Backward Citations)
US3179353A
Cited
US3068646A
Cited
US3040524A
Cited
US3248878A
Cited
US3455111A
Cited
US3262268A
Cited
US3386247A
Cited
US3484847A
Cited
US3614028A
Cited
US3658279A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-11-17 | 1979-05-19 | 1979-11-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-11-17 | 1983-05-19 | 1983-11-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-11-17 | 1987-05-19 | 1987-11-18 | $7700.00 | Window Closed / Lapsed |