JP4944270B1 - Turbo shaft engine V / STOL machine - Google Patents

Abstract

A tilt-rotor aircraft, a tilt-fan aircraft, and a turboshaft that perform vertical and short-distance take-off and landing and departure and arrival from an aircraft carrier. Provide V / STOL engine.
A left and right engine is engaged with a variable ducted rotor provided in the left and right main wings of the center of gravity in conjunction with the shaft, and can be turned left and right from tilt control of the duct equipment, vertical and forward and backward tilting and hovering. Switching from ring rotor and fan flight during cruise flight to jet flight with adjustment control configuration, gradually increase the jet ejection amount, stop the drive shaft to the ring rotor and fan with clutch and rotation with brake, ducted The ring rotor and fan equipment are sealed with the main wing upper and lower sliding doors.
[Selection] Figure 2

Description

It relates to the structure of turbo shaft engine V / STOL machine.

Departures other than V / STOL aircraft are launched by means of catapult propulsion and full power.

Japanese Patent Application 57-48155 Combined engine with convertible output Actual Application Sho 61-94406 Patent No. 2700734 Vertical take-off and landing aircraft Patent No. 3677748 Aircraft created by fixing the rapid airflow generating wind direction changing device directly on the side or side wall of the fuselage. Japanese Patent Application 2011-113112

The existing VTOL turbofan engine was made an auxiliary equipment for vertical levitation by applying the wind power of the fixed and portable prime mover ducted fan to the fuselage volume surface. The VTOL tilt rotor machine and fan machine of the present application are equipped with a small-diameter ducted ring rotor and ring fan that are fixed in the upper part of the fuselage main wing and stored in the main wing separated from the engine. For flight, vertical takeoff with two fixed left and right turboshaft engines, free turbine room with open sliding door structure, and turbo fan engine with bypass ratio engine fan door opening and closing appropriately, jet flight and rotary flight A combination of selected flight configurations.

The composite engine capable of converting the output of Patent Document 1 uses a free turbine with variable blade control, and unlike a helicopter rotor hub mechanism that is variable at the center, links multiple turbine blades that rotate at high speed. At the same time, the control method for making all wings variable is for a rotating machine with low rotation and low safety, and is an unreasonable technique that cannot be used in the center of an airplane engine. In the present application, an annular cover portion is used as a slide door, and the structure has no problem in safety.

If a new short-range launching device that can launch is possible, the number of personnel will be reduced, and all advantages will be achieved.
Patent Document 5 discloses that a fixed-wing, fixed-engine carrier-based aircraft (fighter) launches a large-sized aircraft from an existing aircraft carrier with a small hull such as a diesel engine. As a catapult of levitation, jet propulsion, magnetic levitation, and linear motor, the aircraft body is placed on the air cushion float base from the fan equipment of the optimal prime mover (turbo shaft engine), and the machine friction is eliminated and gliding with the thrust of both engines The catapult device to be used.

The present application also enables the launch of larger aircraft from existing aircraft carriers, and ships and land-specific VTOL aircraft have a small diameter of ring rotor machines and ring fan machines that tilt separately from the engine. A variable ducted rotor, equipped with a fan, a sliding plate sealed structure that is housed in the left and right main wings, a gear connected to a turboshaft engine fixed on the left and right main wings, and combined use of vertical and horizontal takeoff and landing, and rotor From the flight as a plane or fan, gradually switch from the ejection of the open sliding door of the free turbine room to the jet flight, and the ducted rotor is stored in the main wing to increase the speed of the jet flight, and the horizontal takeoff and landing from the jet flight It was supposed to be possible. In addition, it is equipped with a portable fan that helps to lift the burden of the V / STOL turbofan engine and assists the engine output of landing, and can take off from the small hull and take off and landing from the inside. .

Then, avoid the fuel tank and the equipment on the lower part of the fuselage fuselage of the VTOL aircraft mounted on the turbofan engine, and make the lower part of the full fuselage the structure of the deployment door, the structure of the fan levitation and jet propulsion, and the linear motor catapult With the combined use of towing, the launch of wind power, air cushion float and airframe engine output from the front of the ship speed is very small, the launch distance without the burden of the engine is very small, the landing deck distance plane is marginal The ship speed can be set at normal speed, or can be launched in a stopped or moored state, and the various hydrofoil devices and tank cylinder vibration reduction devices described in Patent Document 5 are waves. Easier to launch, speeding up the aircraft from strong winds, making it easier to launch. And the portable fan equipment that assists the levitation output to reduce the burden on the VTOL aircraft makes it easy to take off and land from any location.

Most of the propeller aircraft of claim 1 are turboprop engines, the helicopter is a turboshaft engine that transmits almost 100% to rotational force, and the engine of the tilt rotor aircraft and tilt fan aircraft of the present application is Using a turboshaft engine, the free turbine chamber has an annular sliding door structure. Then, we made a wide-blade small-diameter variable ducted ring rotor blade machine and a multi-blade ring fan blade machine with a smaller diameter. The twin-engine turboshaft engine is fixed at the center of gravity on the fuselage side of the upper left and right main wings. The left and right engines and the ring frame are linked to the shaft, and the variable ducted equipment in the left and right main wings is a free turbine. The two-shaft shaft from the gear is engaged with the ring rotor and ring fan in the duct equipment in the main wing from the gear reduction and direction change gear equipment, the inside of the wide wing is the fixed axis, and in the duct equipment that rotates tilt Rotor hub control with a wide blade area from 4 to 6 blades and ring rotor blades, with a ring frame and rotor blade tips fixed at universal joints, and each rotor blade attracting the ring. The ring / rotor variable angle and variable pitch blade control of the mechanism were adopted. Multi-blade 8-20 fixed ring fan blades are equipped with smaller diameter ducted ring fans, and both blades are equipped with variable ducted equipment to control vertical, forward and reverse tilting and hovering. The turboshaft engine can be turned left and right, and the hub shaft speed reducer and variable pitch front fan blades connected to the compressor shaft in the air intake duct and 8 to 10 blade blades can be opened and closed. It is a bypass passage for door control, a turbofan engine structure that surrounds the compressor, combustion section, and turbine section. The free turbine chamber is a chamber that has a width in the shaft insertion section of the high-pressure turbine. A circular plate structure for jetting into the free passage, and a structure that smoothly jets into the bypass passage. The door can be expanded and contracted by a hydraulic cylinder, the rotation of a hydraulic motor, the expansion and contraction of an electric cylinder and a preliminary mechanical rotation, and the ring rotor and ring fan rotation connected to a free turbine and a shaft from one of the control devices of the annular slide door. The ratio of force and jet spray output is variable, and this door opening / closing becomes an engine of choice of rotational propulsion and jet propulsion, and an opening / closing valve provided on the annular sliding door of the free turbine chamber as appropriate, and the front fan The injection nozzle from the on-off valve of the bypass section is installed at the appropriate position on the main wing, horizontal tail, etc. to make it an auxiliary equipment for levitation, and switching from hovering ring rotor and fan flight to jet flight is a ring in the free turbine room From the sliding door and front fan opening / closing door control, the jet ejection amount gradually increases and the ring rotor, fan The drive shaft to the clutch is stopped, the rotary brake is fixed, the ducted equipment is stored in the main wing of the upper and lower sliding doors, and the free turbine chamber sliding door is fully opened as a turbojet engine, variable pitch The air volume adjustment of the front and rear fan blades and the two open and close doors on the inner and outer surfaces is a bypass ratio engine that enables jet propulsion with an arbitrary air volume, and a turbo fan with a jet propulsion speed that is suitable for the aircraft speed. It becomes an engine, and the ducted equipment is stored, the main wing surface is sealed with the sliding doors on the upper and lower wing surfaces, and it becomes a horizontal take-off and landing aircraft from a jet-propelled flight with high speed, and the jetted equipment is deployed from the wing and jet ejected The half-open control flight of the sliding door is performed by the jet propulsion and the rotor propulsion. It becomes a STOL aircraft of the combined turboprop engine, and the full closing of the free turbine chamber jet ejection slide door becomes a single flight with ducted equipment, and the combined use with thrust of low bypass ratio, turboshaft engine and turbofan The engine is a V / STOL machine, and the output is increased by controlling the variable front fan and each open / close door and fully opening the annular slide door to the turbojet afterburner engine, and various control devices linked to it. A twin-rotation turbo-shaft engine tilt-rotor and tilt-fan aircraft that make it easy to take off and land and take off.
That is, the present invention is a turbo-shaft engine rotor and fan flight and a turbo-jet engine to turbo-fan engine flight, the ducted equipment is not housed in the main wing, and the rotation of the rotor flight is from the turbo-prop engine to the turbo-fan. The ratio of rotation and jet propulsion to switch to the engine is variable, and this tilt rotor machine is a turboshaft engine VTOL machine in a place without a runway. This is a tilt-rotor aircraft that has a small-diameter ducked rotor provided in the main wing, which is a short-range take-off and landing in a turboprop engine. A small number of passenger planes for short-range transport of wing blade fan machines, no runway, and , Faster than existing tilt-rotor machines.

The invention of claim 1 is a ducted ring rotor and ring fan equipment that tilts in the left and right main wings, and the invention of claim 2 eliminates the duct equipment and the ring rotor and ring fan equipment in the main wing. Was fixed horizontally. The twin-engined turboshaft engine V / STOL airplane is equipped with a vertical levitation fuselage by connecting a shaft with a ring rotor or ring fan that is fixed in the main wing from a speed reduction and direction change device. Fine adjustment control of the stable horizontal levitation of a ring rotor and fan equipped aircraft that does not tilt is provided with an opening / closing valve and an opening / closing valve for the front fan section on the annular slide door of the free turbine chamber of the aforementioned turboshaft engine. The nozzle pipe of the caliber is connected to each part such as the left and right main wings, the tip of the horizontal tail, the tip of the fuselage, and the rear part, and the jet jet outlet of the piping is separately constructed, and the vertical levitation is hovering stable at 70% of both engine outputs. The forward speed increases the engine output, and the jet output gradually increases from the annular slide door and front fan opening / closing control of the free turbine chamber to the forward speed. The rotor and fan equipment are fully open and the clutch is stopped and the rotary brake is fixed. The jet engine from the free turbine chamber of the twin-turbo-turbo engine with the structure of jet flight from the VTOL levitation to the VTOL floating, and the above-mentioned variable pitch and deceleration front fan part inside and outside two The opening and closing door and fuel-adjusted low bypass fan engine can also be used. Increased output can be achieved by using a fully open turbojet afterburner engine with an annular sliding door, and an appropriate volume lowering door for deployment. The fan wind power from the prime mover ducted fan equipment is used as an auxiliary to the lift force at the time of takeoff departure from the vertical flight of the fuselage, and the upper air opening and closing air supply duct of the air cushion levitation propulsion float departure equipment is released. Equipped with ship location. A turboshaft engine that consists of jet flight from VTOL ascent and selection of jet take-off and landing, and open / close control of the free turbine room of an all-weather twin-engine V / STOL aircraft.

The VTOL tilt rotor, fan engine, rotor, and fan equipment are separated, and the free turbine (power turbine) chamber of the turboshaft engine is structured as an open door jet and front fan bypass mixed propulsion engine. , Jet flight and rotor flight combined and selected.

Schematic of V / STOL aircraft and turbojet engine. [Embodiment 1] (Fig. A) Schematic view seen from the front of a tilt duct ring rotor blade machine. (b) Schematic view from the front of the tilt ducted ring fan blade machine. (c) Schematic plan view of tilt ducted ring rotor machine. (d figure) The front schematic of a tilt ducted ring rotor and a fan machine. (e figure) Schematic of the wire structure of the sliding door of the duct part in the main wing of a tilt ducted ring rotor and fan machine. (f figure) The plane schematic diagram of the structure of the sliding door of the tilt ducted ring rotor and the main wing duct of a fan machine. (g) Schematic of the structure of a tilted ring rotor and turbofan engine for a fan. (h) Schematic of the structure as seen from the front of the tilt ducted ring rotor and fan machine. Schematic of a ring rotor, ring fan equipped machine that is horizontally fixed in the main wing. [Example 2] (Fig. I) A schematic plan view of a ring-wide rotor machine. (j figure) The plane schematic of opening of the fuselage lower volume door of a ring fan machine. (k) Schematic of the sliding door equipped with the ring and fan on the lower wing surface. (Figure l) Schematic diagram of the structure of a ring rotor and turbomachine of a fan machine. Schematic of deployment of the lower part of the fuselage of the VTOL machine. [Embodiment 3] (Fig. M) Schematic diagram of airframe floating by installing fixed and portable prime mover ringed ring fan equipment under road surface. (n figure) The front view which stored the fuselage expansion | deployment door of the said ring rotor, ring fan equipped machine. (o) Expanded the volume door on the lower surface of the tilt ring fan machine

  This will be described based on the drawings and reference numerals.

The propeller aircraft is a turboprop engine, the helicopter is a turboshaft engine, and the twin-engine tilt-rotor aircraft (S1) and fan (S1) aircraft of this application in [Fig. 1] (Fig. 1a, b, h) The turboshaft engine (B) is fixed to the upper part of the main wing surface at the top of the fuselage, and the ducted ring rotor is inserted into the left and right main wings from the free turbine and the front shaft deceleration and direction change (36) mechanism. Or use a ring equipped with a fan, a ring / wide rotor blade (U) frame, or a multi-blade ring / fan blade (T) frame. The upper and lower wings are sealed with sliding doors (28), and the annular sliding door (Y) of the free turbine chamber (X) in (g) is opened and closed with a hydraulic cylinder, motor or electric cylinder, motor and spare machine manual. Structure and half-open jet The combination of propulsion and ducted ring rotor and fan rotation propulsion becomes a turboprop engine machine, and the variable pitch and deceleration front fan blade hub device (35) in the air intake duct connected to the compressor shaft is The open turbine door (flap) (32) is provided in the bypass passage, and the free turbine chamber (X) fluidly connected to the compression turbine section from the combustor is opened by the annular slide door (Y) to make jet ejection. The chamber of the free turbine circumferential plate (29) that sets a slight distance, the bypass passage (31) as a support frame, the open / close door (32) fully open and the free turbine section slide door fully open are low. The bypass turbofan engine is used, and the free turbine chamber is fully closed by rotating the rotor and fan of the turboshaft engine.
The annular sliding door (Y), the speed reduction variable pitch hub (35) output of the front fan (30), and the fine adjustment opening / closing of the inner opening / closing door (32) and the outer opening / closing door (56) are any of the above. The jet engine form, and the output increase is the turbo jet afterburner engine (57), horizontal take-off and landing can be done with the configuration of both rotary propulsion and jet propulsion engines, and the speed of horizontal flight, It will be an all-weather vertical takeoff and landing aircraft.

And, the assumed aircraft weight is 30 tons, and the twin-tilt turbo engine with a 30-crew engine is equipped with a free turbine and a variable ducted ring rotor with a shaft connection. The ring fan equipment will be smaller, with a maximum of about 5.0M, and will be a vertical and horizontal take-off and landing tilt rotor and fan machine that will fit in a main wing with a maximum front and rear width of about 70cm and a maximum height of about 70cm.
The ring-rotor machine of the rotor hub control mechanism (39) uses duct variable angle and variable pitch blade control, and the fixed ring fan blade of the multi-blade 8 to 20 is equipped with a ducted ring fan with a smaller diameter.
Featuring a helicopter convenience and noise-fitting horizontal flight turbofan engine, a tilt-rotor that houses all-weather storage, and a fan-equipped turboshaft engine jet.
The twin-engine tilt-rotor machine, which will be a V / STOL machine, is equipped with a ring-wide rotor-equipped lift blade and a small-diameter variable ducted ring rotor. The lift configuration provided in the appropriate position, the variable ducted ring rotor equipment, the configuration that fits in the main wing outside the engine, and the variable rotation of the hydraulic motor at an appropriate angle above and below the variable duct with the left and right bearings (41) In the variable duct, the ring / rotor equipment rotating in the duct is connected to the variable gearbox of the drive shaft from the speed change and direction changing mechanism in the front of the engine. It is assumed that it has a main wing area that can perform rotor flight landing and jet flight with one engine output at the time, and model selection from this engine output and fuel consumption is Compared with helicopters, propellers, jets and the efficiency, and this application is a tilt ring rotor machine in which the variable duct is housed in the main wing in the rotating hydraulic equipment for duct, and the above-mentioned appropriate fuselage lower surface Is a volume wind power deployment door (V), and a fixed, portable prime mover equipped with a ducted fan (R) is used as an auxiliary structure for floating by wind power.

And the ring rotor equipment can move backwards and swivels from the surface of the blade with a wide area and variable duct, can move backwards and swivels vertically, and can run and take off and land smoothly. In horizontal cruise flight, switching from turboprop flight to turbojet flight, the adjustment control of the annular slide door (Y) becomes the rotor rotation and jet ratio, and the ring rotor rotation is clutched The stop (38) and rotary brake (40) are fixed, and the turbo-jet engine flight is achieved when fully open, and the tilt ring rotor machine is achieved when fully closed and the clutch is input. During turbojet flight, the variable ducted ring rotor equipment part slides the sliding door (28) of the main wing from the fuselage internal storage on the upper surface of the fuselage and the lower surface of the left and right main wings to the wing circumference of the duct frame (W). The support slide deployment frame (54) for the hydraulic / pneumatic cylinder deployment from the circumference of the main wing is used as a guide and support, and electric or hydraulic motor winches are installed at appropriate positions on the main wing and fuselage, and the slide (upper and lower) is supported by the wire (53). The cover door is wrapped around two cover winches to form a closed and open wire structure, or a plurality of hydraulic telescopic cylinders can be expanded and contracted. The total area of the left and right main wings is enough to lift and lift up the speed. Also, the airplane will be a short-distance section of rotor, fan rotation and jet propulsion, and a medium-distance section of jet propulsion, and the landing will be made by horizontally landing the turbojet with the sliding door closed or switching to the ducted rotor flight. Vertical takeoff and landing in a place without a runway, horizontal takeoff and landing on a runway, and takeoff and landing of a short distance with the above-mentioned V / STOL fuselage expansion volume door, from the ring rotor From the blade area, it is a tilt ring rotor machine with a small caliber ducked ring rotor equipment.

And, it is possible to take off and land from any land and indoor from small ships, and equipped with variable ducted rotor equipment on the main wing part and small ducked rotor equipment or turbofan engine on the left and right of the rear of the aircraft Set up a vertical take-off and landing of large passengers and transport aircraft 50t, and open / close valves (33) on the sliding door (Y) of the free turbine room and opening / closing valves (32) on the front fan bypass opening / closing door (32) as appropriate. 55) is provided for communication, or separate nozzles (37) of various calibers are provided at appropriate positions such as the fuselage, main wing, horizontal tail, etc., to assist in ascent.
The tilt and ring rotor and turbine jet engines are designed to ensure speed and safety and add speed to the convenience of the helicopter.
The current tilt-rotor machine has an engine and rotor blades integrated, and the fixed main wing and the engine must be variably controlled from a mechanism that makes the engine variable by about 100 degrees. Is a fixed engine, and the difference in maneuverability and safety is clear when compared to jet flight during cruise flight. When STOL sliding take-off and landing of the turboprop flight is performed, noise is reduced and fuel consumption is improved. It became the tilt rotor machine.

Unlike the helicopter rotor blade and propeller airplane blade, the ring rotor and fan equipment of (a, b) can be made small in diameter and as a propeller that is fixed separately with a shaft connection with the turboprop engine. Since the main wing is inevitably stored in the main wing, the thickness and width of the main wing are increased, and the strength of the tip is ensured. The fuselage, the left and right main wing frames, and the duct frame frame are integrated into a single metal frame. And the wing tip has a structure such as wire or piano wire.

The ring rotor and fan equipment (S2) shown in [Fig. 2] are fixed horizontally in the main wing instead of the ducted ring rotor and fan equipment (S1) tilted in the left and right main wings as described in Example 1. For fine-tuning control of the aircraft, the open / close valve (33) is provided on the annular slide doors of the left and right turboshaft engine free turbine chambers described above. 37) shall be ejected from the pipes at the left and right main wing tips and the fuselage tip fuselage rear part, and the opening and closing valves (55) and the opening and closing valves (33) of the above-mentioned variable pitch and deceleration front fan part. (37) is separately or communicated, and the main wing from the jet engine ejected from the free turbine of the twin-engine turboshaft engine with the structure of jet flight from the rise of VTOL has the above-described upper and lower slide cover (28) sealed structure. ,free The jet injection volume gradually increases from the control of the annular sliding door (Y) in the turbine room, the inner door (32) and the outer door (56) in the front fan section, and the low bypass fan engine with air volume and fuel adjustment The fan from the fixed and portable prime mover ducted fan equipment (R) described above, with the lower body part of the fuselage as the above-mentioned appropriate floating support in FIG. The wind force was used as an auxiliary to the levitation force at the time of takeoff and departure from the aircraft vertical, and the upper and lower ducts on the air cushion float launch equipment were used as the place of departure.

This airframe will be hovering stable at levitation with an engine output of 70%, jet jets will gradually increase from the opening of the annular slide door (Y) of the free turbine, and the slide door and the open / close door (32) will be fully opened. 100% of the flight, with the ring rotor and fan equipment fully open, the clutch (38) and rotary brake (40) are stopped, and the main wing is sealed with the above-mentioned upper and lower slide covers (28). Jet engine jetted from free turbine of twin-turbo-turbo engine with floating to jet flight configuration, front and rear doors (32) and outer doors (56) of variable pitch and deceleration front fan, and fuel adjustment From the rise of VTOL and the choice of jet flight configuration and jet take-off and landing to an all-weather twin-engine V / STOL aircraft, control is hydraulic, electric actuated A turboshaft engine airplane consisting of a turbojet and afterburner engine (57), and a free turbine chamber opening and closing control, with a spare and a mechanical system as a reserve.

In the control of the engines of Examples 1 and 2, the free turbine chamber of the turboshaft engine was an annular sliding door. The sliding door is opened and closed from jet flight to jet flight. The front and rear widths of the two-shaft shaft shaft inserted into the compression turbine shaft at the front of the free turbine are provided, and the free turbine plate has a circumferential frame structure. Therefore, the sliding door is fully opened and ejected into the bypass passage by force due to the resistance of the blade surface.Slight door opening / closing ratio and full opening and closing are the rotation of the blade surface and the jet ejection. The ratio is variable, with a few millimeters of control and a rapid hydraulic flow control of 3cm and an electric screw cylinder method. It was supposed to be.
Making the rotor and fan equipment variable and fixed in the main wing, ensuring the width, thickness, length and strength of the main wing is the biggest challenge, the blade area from the reduction ratio of the ring rotor and fan, A wide rotor and a multi-blade fan with a small diameter as much as possible, and a high-rotation output, fits in the main wing, and the main wing has an open / close cover structure. In this control and maneuvering, the turboshaft engine can be used with the engine output from the fixed to the upper part of the fuselage, and the configuration of fixing the ring rotor and fan to the main wing of Example 2 The weight is reduced, and a nozzle jet outlet for fine adjustment of horizontal levitation is provided at each part, which is simpler than the ducted ring rotor variable machine of the first embodiment.

In the jet engines of Examples 1 and 2, jet airplanes are mainly turbofan engines with a high bypass ratio due to noise and fuel consumption, and aircraft that require a long runway have a certain airfield, The cost is enormous and has a mass consumption structure. In the V / STOL machine described in Examples 1 and 2 of the present application, when the weight of 50 to 100 passengers and the weight of 50 tons is safely taken off and landing in a small space at a speed of 700 km / h, the transportation form changes.

The powerful ducted equipment with small caliber for vertical and horizontal takeoff and landing that is installed in the main wing from the turbo shaft engine of the V / STOL tilt ring rotor aircraft and fan aircraft of this application is enclosed and sealed in the main wing during horizontal cruise flight, Opening the free turbine chamber of the shaft engine and switching from the front fan bypass ratio to the turbofan engine, it becomes a jet-propelled horizontal flight and gliding take-off and landing aircraft, the speed of the all-weather turbine jet and the tilt ring rotor It will be a convenient machine for fan machines. In addition, the ring rotor and fan equipment are fixed in the main wing, and each part is made into a V / STOL airplane of a twin-shaft turboshaft engine that is lightweight and simple for jet forward flight from hovering of jet nozzle ejection from the free turbine chamber. .

Making the ducted ring rotor equipment of the tilt ring rotor machine into a universally connected ring rotor blade makes the blade angle almost constant even if the engine output is increased, and the rotor hub similar to a helicopter From the control (39), the angle of the ring rotor is changed. With this ring frame free fixing method, the blade width can be widened, and the ducted ring rotor can be equipped with a small small diameter rotor that can be installed in the main wing, can be fixed separately from the engine, and the above-mentioned jet shaft engine Appropriate take-off and landing and departure and landing with the air cushion device.

With the free turbine part of the turboshaft engine as the chamber, the opening control equipment is configured as a turboprop engine that opens the annular slide door and the ratio of propulsion shaft shaft rotational force and jet spray output is variable. When the door is fully open, the jet of the turbojet engine is ejected, and the front fan with variable pitch connected to the compressor shaft and the reducer in the air intake duct has an appropriate bypass ratio that matches the speed of the aircraft from the open / close door on the inner and outer surfaces. It becomes a turbofan engine, and an open / close valve is provided on the sliding door of the free turbine room and on the front fan part. / STOL amphibious aircraft, tilt aircraft, helicopters, air cushion boats, ships, amphibious vehicles, etc. The adoption of a combination of various cushion emerged. In addition, it is also possible to increase the output by 100% jet ejection by fully opening the annular sliding door of the free turbine chamber and the rear part as an afterburner combustion part.

This turboshaft engine helicopter is a free turbine engine that opens and closes the sliding door of the free turbine chamber. By finely adjusting the opening and closing, the levitation propulsion force of the rotor blades is 50% and jet jet propulsion is 50%. Then the speed will be increased, and the rotor and two engines from two free turbine engines will be jet propulsion, and it will be a new all-weather jet helicopter with ample output.

B turboshaft engine QV / STOL turbofan engine
R fixed and portable prime mover with ducted fan S1 tilt ring rotor, fan machine
S2 main wing fixing ring / rotor, fixing machine with fan T multi-wing ring / fan blade
U ring wide rotor blade V fuselage lower volume door W duct frame
X free turbine chamber Y annular sliding door (open / close) Z annular support frame

28 Sliding doors on the upper and lower main blade surfaces 29 Free turbine circumferential plate 30 Front fan blade
31 Bypass passage 32 Open / close door (flap) in bypass section 33 Open / close valve on annular slide door 34 Float outlet 35 Front fan deceleration variable pitch hub device 36 Deceleration and direction change equipment 37 Nozzle outlet 38 Clutch 39 Hub mechanism 40 Rotating brake 41 bearing 53 wire
54 Slide frame 55 Open / close valve 56 Open / close door on the outside 57 Afterburner

Claims (2)

In the twin-engine turboshaft engine (B), the left and right main wings are fixed to the upper part of the fuselage, and the center of gravity of the fuselage side of the upper part of the left and right main wings is fixed. Is either the ring rotor (S1) or the ring fan (S1) of the variable pitch blade in the variable duct of the tilt equipment that is stored in the left and right main wings from the free turbine 2-shaft shaft reduction direction change equipment (36) From the vertical levitation of engagement to the configuration of rotary flight and the opening and closing control of the annular slide door (Y) that opens the free turbine chamber (X) to the configuration of jet propulsion flight, the configuration of both flights is the slide door (Y) Shifting from hovering to jet flight with a variable engine that can be used in combination with tilt rotation flight and jet propulsion flight by adjusting the opening and closing of the two-axis drive and engaging / disengaging the clutch (38) of the biaxial drive shaft and controlling the rotary brake (40) Is An open / close valve (33) provided on the annular slide door (Y) and an open / close valve (55) provided on the open / close door (32) of the front fan (30) of the speed reduction and variable pitch device (35) are provided on each part of the fuselage. Equipped with a posture control equipment that communicates with the ejection nozzle (37), gradually open the free turbine chamber (X) door, and open the front fan open / close door (32) for bypass ratio fan engine flight, tilt rotation flight The turboshaft is composed of a vertical take-off and landing by the aircraft, a horizontal take-off and landing by jet flight and rotary flight, and the variable duct equipment is sealed with sliding doors (28) on the upper and lower surfaces of the main wing and equipped with various control devices. Engine V / STOL machine. The V / STOL machine of the twin-engine turboshaft engine (B) is either a ring rotor (S2) that is horizontally fixed in the main wing from the speed reduction and direction change equipment (36), or a ring fan (S2). Engage and fly, the position adjustment jet nozzle (37) is provided at each part, and the structure of vertical take-off and landing by either a ring rotor or a fan, the clutch (38) engagement and rotation brake from the rising (40) The free turbine chamber (X) and the open / close door (32) are gradually opened from the control to form a bypass ratio fan engine, and an afterburner engine with increased thrust, and the turboshaft engine according to claim 1, V / STOL machine.

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