JP2003028005A - Turbo-fan engine and vertical takeoff and landing aircraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To realize an unwasteful and rational structure regarding heat resistance of a material, to facilitate a design and suppress a whole cost including a cost of the material by dividing respective nozzles for by-pass air and jet in a turbo-fan engine having a vertical takeoff and landing function. SOLUTION: The turbo-fan engine E is provided with a by-pass-nozzle 3 for injecting by-pass air of low temperature passed through a fan 21 and injected as it is and a jet nozzle 27 for injecting jet of high temperature passed through a compressor from the fan 21 and burned. The by-pass nozzle 3 has a downward injection port 33 capable of downwardly injecting the by-pass air and a horizontal injection port 32 capable of horizontally injecting the by-pass air. The downward injection port 33 and the horizontal injection port 32 are constituted such that they can selectively inject the by-pass air to a downward direction and a horizontal direction by blocking one side by a blocking body 34. The jet nozzle 27 is constituted such that the jet can be downwardly injected.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbofan engine and a vertical takeoff and landing aircraft. More specifically, in a turbofan engine having a vertical take-off and landing function, low-temperature air that is directly injected through a fan (bypass air) and high-temperature air (jet) that is burned and injected from a fan through a compressor Each of the nozzles is divided into a rational structure with no waste in terms of heat resistance of the material.

[0002]

2. Description of the Related Art Conventionally, an aircraft that does not require a runway or can take off and land by a short run, and can fly at a subsonic speed or more (the former is a vertical takeoff and landing vehicle (VTOL: v
ertical take‐off and landing air), the latter is a short take‐off and landing air (STOL).
craft))). Such aircraft are, for example, business aircraft, emergency disaster prevention aircraft, search and rescue aircraft, maritime security rescue aircraft,
Or it is used as a government-only machine.

Among these, a gas turbine engine mounted on a vertical take-off and landing aircraft (VTOL) is one in which the direction of the engine itself changes during vertical take-off and landing and during horizontal flight (a turboprop engine is adopted), The direction of the engine does not change between vertical takeoff and landing and horizontal flight, and only the direction of the nozzle changes (a turbofan engine is adopted).

The latter turbofan engine has a low fuel consumption rate and high overall efficiency. The turbofan engine uses low-temperature air (bypass air) that is directly injected through the fan and high-temperature air (jet) that is burned and injected from the fan through the compressor as thrust. The air of this is jetted from a common nozzle in the same place.

[0005]

However, the conventional turbofan engine and vertical take-off and landing aircraft as described above have the following problems. That is, low-temperature air (bypass air) that is directly injected through the fan and high-temperature air (jet) that is burned and injected through the compressor from the fan are injected from a common nozzle in the same location. Therefore, the air that is directly injected through the fan does not have a high temperature, but it is mixed and heated to a high temperature by using a nozzle common to the high-temperature jet. Therefore, as a result, the nozzle and the entire necessary portion in the vicinity thereof have to be made of an expensive material (metal, ceramic, etc.) having high heat resistance. Further, it is not easy to design considering the thermal expansion of the movable part, and the total cost including material cost is high.

(Object of the Invention) The object of the present invention is, in a turbofan engine having a vertical take-off and landing function, low-temperature air (bypass air) directly injected through a fan and combustion from a fan through a compressor. By separating each nozzle of high-temperature air (jet) that is jetted as a result, a high-heat-resistant and expensive material is used only in the nozzle that jets high-temperature air and in the vicinity thereof, and a nozzle that jets low-temperature air. The turbofan engine and the turbofan engine that can reduce the total cost including the cost of materials by simplifying the design by adopting a rational structure that does not waste heat resistance of materials It is to provide the vertical take-off and landing aircraft used.

[0007]

[Means for Solving the Problems] The means of the present invention taken to achieve the above object are as follows. According to the first aspect of the invention, a bypass nozzle that injects low-temperature bypass air that is directly injected through the fan and a jet nozzle that injects a high-temperature jet that burns from the fan through the compressor are provided. And the bypass nozzle is
It is a turbofan engine characterized in that bypass air can be selectively jetted downward and horizontal, and the jet nozzle can jet jets downward.

In the second aspect of the invention, a bypass nozzle for injecting low-temperature bypass air that is directly injected through the fan, a jet nozzle for injecting a high-temperature jet that burns from the fan through the compressor, Is equipped with
The bypass nozzle has a downward injection port capable of injecting bypass air downward, and a horizontal injection port capable of horizontally injecting, and the downward injection port and the horizontal injection port have one side with a blocking means. By blocking, bypass air can be selectively injected in the downward and horizontal directions, and the jet nozzle is capable of injecting a jet in the downward direction. is there.

According to a third aspect of the present invention, there is provided a vertical take-off and landing aircraft which is equipped with the turbofan engine according to the first or second aspect of the invention.

According to a fourth aspect of the present invention, a plurality of turbofan engines are mounted, and the output of each turbofan engine is adjusted so that the vertical take-off and landing aircraft can take off and land while maintaining a horizontal state. It is a vertical takeoff and landing aircraft according to a third invention.

The bypass ratio (a value obtained by dividing the amount of bypass air by the amount of jet air) of the turbofan engine according to the present invention is not particularly limited, but is generally about 3 to 6. The performance of the turbofan engine changes depending on the bypass ratio, and generally, as the bypass ratio increases, the propulsion efficiency improves and the fuel consumption rate decreases.
The turbofan engine according to the present invention can be used not only as an actual vertical take-off and landing aircraft but also as an engine for a vertical take-off and landing aircraft of a model airplane by downsizing.

(Operation) The turbofan engine according to the present invention has a vertical takeoff and landing function, and has low-temperature air (bypass air) that is directly injected through the fan and is burned and injected through the compressor from the fan. Each of the hot air (jet) nozzles is divided into a bypass nozzle and a jet nozzle. Therefore, use a material with high heat resistance only for the jet nozzle that injects high-temperature air and its vicinity, and not for a bypass nozzle that injects low-temperature air. By adopting the structure, the design can be facilitated and the total cost including the cost of the material can be suppressed.

To vertically raise the vertical take-off and landing aircraft equipped with the turbofan engine according to the present invention, first, the engine is started. The bypass nozzles are selected in the downward direction so that the bypass air can be injected in the same downward direction as the jets by the jet nozzles. Then, the output of the engine is increased to inject the bypass air and the jet downward. As a result, the vertical take-off and landing aircraft can take off and rise vertically while maintaining a horizontal state.

When the aircraft moves to horizontal flight after climbing to a predetermined altitude, the bypass nozzle is selected in the horizontal direction and injects bypass air in the horizontal direction (direction opposite to the flight direction). The thrust of the vertical take-off and landing aircraft is obtained by bypass air, and the lift is obtained by the downward jet from the wings and jet nozzles.

When landing, as in the case of vertically rising, the bypass nozzle is selected in the downward direction, the bypass air is injected in the same downward direction as the jet from the jet nozzle, the injection amount is adjusted, and the horizontal state is achieved. While descending,
To land.

[0016]

BEST MODE FOR CARRYING OUT THE INVENTION The present invention will be described in more detail based on the embodiments shown in the drawings. FIG. 1 is an explanatory view showing the structure of a jet engine according to the present invention. Reference E is a turbofan engine having a fan on the front side. The turbofan engine E includes a duct 1. The duct 1 is formed in a substantially cylindrical shape. Inside the duct 1, an engine body 2 is attached by means of attachment ribs 10.

The engine body 2 has an engine duct 20. A shaft (not shown) is axially supported by the engine duct 20, and a fan 21 is provided at the front end of the shaft. A low pressure compressor 22 and a high pressure compressor 23 are provided on the rear side of the fan 21. A combustion chamber 24 is provided on the rear side of the high pressure compressor 23.

A high-pressure turbine 25 for driving a fan and a low-pressure turbine 26 for driving a compressor are provided on the rear side of the combustion chamber 24. A jet nozzle 27 is provided at the rear of the engine duct 20. The jet nozzle 27 is bent downward, penetrates a wall portion of an airway portion 30 described later, and can jet a jet downward. The jet direction of the jet nozzle 27 is normally vertically downward, but is not limited to this as long as the vertical take-off and landing aircraft equipped with the turbofan engine E can vertically take off and land.
The jet nozzle 27 may be a movable type that can change the jetting direction.

A bypass nozzle 3 is connected to the rear end of the duct 1. The bypass nozzle 3 has a tubular straight air passage portion 30 and a hollow, substantially spherical exhaust passage portion 31 provided at the rear portion thereof. As described above, the jet nozzle 27 penetrates the wall portion of the airway portion 30. A circular horizontal injection port 32 is provided at the rear of the exhaust passage 31.
Is provided. A circular downward injection port 33 is also provided in the lower portion of the exhaust passage portion 31. In addition, in the exhaust passage portion 31,
A sealing body 34 that moves in an airtight state (at a contact surface) along the outer surface of the exhaust passage portion 31 is provided. Block 34
Can be pivotally moved in the vertical direction about the shaft 35 to selectively block the horizontal jet 32 and the downward jet 33.

FIG. 2 is a front view of the vertical take-off and landing aircraft according to the present invention, FIG. 3 is a plan view of the vertical take-off and landing aircraft according to the present invention, and FIG. 4 is a side view of the vertical take-off and landing aircraft according to the present invention.

Here, the structure of the vertical take-off and landing aircraft J will be outlined. Reference numeral 4 is a body, 5 is a main wing, 6 is a vertical stabilizer, and 7 is a horizontal stabilizer. The above-described turbofan engines E are provided one by one at the lower portions on both sides of the main wing 5. Further, one turbofan engine E is provided on each side of the rear portion of the body 4. The rear-side turbofan engine E provided on the fuselage 4 is located inside the front-side turbofan engine E provided on the main wing 5, so that the jet of the front-side turbofan engine E directly hits the turbofan engine E. I try not to.

(Operation) FIG. 5 shows the state of the turbofan engine on the main wing side when the vertical take-off and landing aircraft flies,
(A) is a side view explanatory drawing at the time of vertical ascent, descent, or an air stop, and (b) is a side view explanatory drawing at the time of horizontal flight. 1 to 5, the operation of the turbofan engine E according to the present invention and the vertical take-off and landing aircraft J equipped with the turbofan engine E will be described.

To vertically raise the vertical take-off and landing aircraft J, first, each turbofan engine E is started. The downward injection port 33 is selected as the bypass nozzle 3 (the blocker 3
The horizontal jet 32 is blocked by 4) so that the bypass air can be jetted in the same downward direction as the jet by the jet nozzle 27. Then, the output of each turbofan engine E is increased to inject the bypass air and the jet downward. As a result, the vertical take-off and landing aircraft J can take off and rise vertically while maintaining a horizontal state.

At this time, the output or injection amount of each turbofan engine E is set to 60% of the total for the two main wings and 40% of the two for the tail wings. I try to keep it horizontal. The balance setting of this output is also 60% for the two main wings and 40% for the two tail wings when landing to be described later.
It is not limited to this value.

After the vertical take-off and landing aircraft J has climbed to a predetermined altitude and then moves to horizontal flight, each turbofan engine E
In the bypass nozzle 3 of (1), the horizontal injection port 32 is selected (the downward injection port 33 is closed by the closing body 34), and the bypass air is injected in the horizontal direction (direction opposite to the flight direction). The propulsive force of the vertical take-off and landing aircraft J during horizontal flight is obtained by the bypass air, and the lift force is applied to the wings (main wing 5 and horizontal stabilizer 7).
And the jet nozzle 27 provides a downward jet. Since the bypass nozzle 3 is substantially spherical, air resistance during flight is small.

When the vertical take-off and landing aircraft J is landing, the downward injection port 33 is selected for the bypass nozzle 3 and the bypass air is supplied to the jet nozzle 27 as in the case of vertically rising.
It jets in the same downward direction as the jet from, adjusts the injection amount (it becomes weaker when rising), descends while maintaining a horizontal state, and lands. As described above, the vertical take-off and landing aircraft J according to the present invention has the horizontal injection port 3 provided in the bypass nozzle 3.
2 by switching the downward injection port 33 and
It can descend and level, does not require a runway, and can take off and land in a narrow space.

It should be noted that the terms and expressions used in the present specification are merely for explanation and are not limiting, and terms equivalent to the above terms and expressions and expressions are not excluded. The present invention is not limited to the illustrated embodiment, and various modifications can be made within the scope of the technical idea.

[0028]

The turbofan engine according to the present invention is
In a turbofan engine with vertical take-off and landing function, each nozzle of low-temperature air (bypass air) that is directly injected through a fan and high-temperature air (jet) that is burned and injected from a fan through a compressor However, it is divided into a bypass nozzle and a jet nozzle. Therefore, use an expensive material with high heat resistance only for the jet nozzle that injects high temperature air and its vicinity, and not for a bypass nozzle that injects low temperature air. By adopting a general structure, the design can be facilitated. In addition, the total cost including the cost of materials can be suppressed. Furthermore, the vertical take-off and landing aircraft according to the present invention can perform ascending / descending, aerial stop and level flight by switching the horizontal injection port and the downward injection port provided in the bypass nozzle, and requires no runway. Instead, it can take off and land in a narrow space.

[Brief description of drawings]

FIG. 1 is an explanatory view showing the structure of a turbofan engine according to the present invention.

FIG. 2 is a front view of a vertical take-off and landing aircraft according to the present invention.

FIG. 3 is a plan view of a vertical take-off and landing aircraft according to the present invention.

FIG. 4 is a side view of a vertical take-off and landing aircraft according to the present invention.

FIG. 5 shows a state of the turbofan engine on the wing side when the vertical take-off and landing aircraft flies, (a) is a side view explanatory diagram when vertically rising, descending or stopping in the air, (b) is a horizontal flight FIG.

[Explanation of symbols]

E turbofan engine 1 duct 10 Mounting rib 2 engine body 20 engine duct 21 fans 22 Low pressure compressor 23 High pressure compressor 24 Combustion chamber 25 high pressure turbine 26 Low pressure turbine 27 jet nozzles 3 bypass nozzle 30 airway 31 Exhaust Road 32 Horizontal jet 33 Downward jet 34 Blocked body 35 axes J vertical takeoff and landing aircraft 4 torso 5 wings 6 vertical tail 7 Horizontal stabilizer

Claims (4)

[Claims] 1. A bypass nozzle (3) for injecting low temperature bypass air that is directly injected through a fan (21), and a jet nozzle for injecting a high temperature jet that burns from a fan (21) through a compressor. (27) and, the bypass nozzle (3) is capable of selectively injecting bypass air downward and horizontal, the jet nozzle (27), the jet downward A turbofan engine characterized by being able to inject. 2. A bypass nozzle (3) for injecting low temperature bypass air that is directly injected through a fan (21), and a jet nozzle for injecting a high temperature jet that burns from a fan (21) through a compressor. The bypass nozzle (3) has a downward injection port (33) capable of injecting bypass air downward and a horizontal injection port (32) capable of horizontally injecting bypass air. However, the downward injection port (33) and the horizontal injection port (32), by blocking one side by a blocking means, it is possible to selectively blow the bypass air in the downward and horizontal directions, The jet nozzle (27) is a turbofan engine characterized by being capable of injecting a jet downward. 3. A vertical take-off and landing aircraft, comprising the turbofan engine according to claim 1 or 2. 4. A plurality of turbofan engines are mounted,
The vertical take-off and landing aircraft according to claim 3, wherein the output of each turbofan engine is adjusted so that the vertical take-off and landing aircraft can take off and land while maintaining a horizontal state.