CN109779783A

CN109779783A - A kind of fanjet with the autonomous regulating power of bypass ratio

Info

Publication number: CN109779783A
Application number: CN201910274680.9A
Authority: CN
Inventors: 田大可; 金路; 张宇; 范小东; 杨谢柳; 张岩
Original assignee: Shenyang Jianzhu University
Current assignee: Chengdu Nazeda Testing Equipment Co.,Ltd.
Priority date: 2019-04-08
Filing date: 2019-04-08
Publication date: 2019-05-21
Anticipated expiration: 2039-04-08
Also published as: CN109779783B

Abstract

The invention relates to the technical field of aerodynamics, in particular to a turbofan engine with the capability of self-adjusting bypass ratio. The technical scheme is: including a first valve, a fan, a reducer, a second valve, a compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, a third valve, a fourth valve and a fifth valve; the fan is connected to the low-pressure turbine through the reducer The low-pressure rotor system is formed, and the low-pressure rotor system is supported on the first bearing, the second bearing, the third bearing and the sixth bearing; the compressor and the high-pressure turbine are connected to form a high-pressure rotor system, and the high-pressure rotor system is supported on the fourth bearing and the sixth bearing. Five bearings; the first valve is installed on the front end of the second external casing, the second valve is installed on the intermediate casing, the third valve is installed on the rear casing, and the fourth valve is installed on the first external casing. At the rear end, the fifth valve is installed at the rear end of the second outer casing. The invention has strong adaptability, large unit thrust, high propulsion efficiency and low fuel consumption rate.

Description

A kind of fanjet with the autonomous regulating power of bypass ratio

Technical field

The present invention relates to aviation power technical fields, and in particular to a kind of turbofan hair with the autonomous regulating power of bypass ratio Motivation.

Background technique

Aero-engine is aircraft " heart ", is the core component in the big system of aircraft, as the mankind are in national defence, section The continuous expansion of the fields such as grinding, is civilian, to aircraft especially aero-engine multitask, long voyage, high-altitude, in terms of It is proposed new, higher requirement.Traditional regular circulation engine mainly includes turbojet engine and fanjet two Seed type, turbojet engine fully rely on the high-temperature fuel gas stream in duct and generate thrust, are typically used as the power of high-speed flight, but Turbojet engine oil consumption rate is higher, propulsive efficiency is lower；Fanjet is total to by outer culvert fan airstream and intension high-temperature fuel gas stream With thrust is generated, having many advantages, such as that propulsive efficiency is high, oil consumption rate is low, the thermal efficiency and propulsive efficiency balance are good, but major diameter Fan increases the front face area of engine, so that the biggish fanjet of bypass ratio is not suitable for doing supersonic cruise flight. It can be seen that the fixed cycles engine of mesh first two routine it is all different degrees of have some disadvantages and it is insufficient, it is difficult to it is suitable Answer the demand for development of future aircraft.

Summary of the invention

The present invention provides a kind of fanjet with the autonomous regulating power of bypass ratio, has adaptable, unit The advantages such as thrust is big, propulsive efficiency is high, oil consumption rate is low.

Technical scheme is as follows:

A kind of fanjet with the autonomous regulating power of bypass ratio, including the first valve, fan, retarder, second Valve, compressor, combustion chamber, high-pressure turbine, low-pressure turbine, third valve, the 4th valve and the 5th valve；The fan passes through The retarder is connected with low-pressure turbine and forms low pressure rotor system, and the low pressure rotor system is supported on first bearing, In two bearings, 3rd bearing and 6th bearing；The compressor is connected with high-pressure turbine and forms high pressure rotor system, the height Pressure rotor-support-foundation system is supported in fourth bearing and 5th bearing；First valve is mounted on the front end for containing casing outside second, the second valve Door is mounted on Middle casing, and third valve is mounted on rear housing, and the 4th valve is mounted on the rear end for containing casing outside first, the Five valves are mounted on the rear end for containing casing outside second.

Further, the fanjet with the autonomous regulating power of bypass ratio, wherein the first valve passes through hinge The mode connect is mounted on the front end for containing casing outside second, and the second valve is mounted on Middle casing by hinged mode, third Valve is mounted on rear housing by hinged mode, and the 4th valve is mounted on outside first after culvert casing by hinged mode End, the 5th valve are mounted on the rear end for containing casing outside second by hinged mode.

Further, the fanjet with the autonomous regulating power of bypass ratio, wherein first bearing, the second axis It holds, 3rd bearing, fourth bearing, 5th bearing and 6th bearing are magnetic bearing.

Further, the fanjet with the autonomous regulating power of bypass ratio, wherein first bearing is mounted on On front housing；Second bearing, 3rd bearing and fourth bearing are mounted on Middle casing；5th bearing is intershaft bearing, installation Between high pressure rotor system and low pressure rotor system；6th bearing is mounted on rear housing.

The invention has the benefit that the one, present invention is by designing multiple control valves, it can be achieved that between different bypass ratios Continuous conversion, not only meets the requirement of aircraft multitask, while improving the fuel economy of engine；Two, this hair It is bright that retarder is devised between fan and low-pressure turbine, two respective potential of component are effectively played, engine is improved Performance；Three, high and low pressure rotor-support-foundation system of the invention all uses magnetic bearing, which can meet high revolving speed requirement, simultaneously It does not need to lubricate, alleviates the weight of structure；Four, the design philosophy that its multi-mode of fanjet of the invention is adjusted can also answer For fields such as space flight, navigation, automobiles.

Detailed description of the invention

Fig. 1 is the fanjet general structure schematic diagram with the autonomous regulating power of bypass ratio；

Fig. 2 is the first duct list duct operating mode schematic diagram；

Fig. 3 is the first duct and the double duct operating mode schematic diagrames of the second duct；

Fig. 4 is the first duct and the double duct operating mode schematic diagrames of third duct；

Fig. 5 is that the first duct, the second duct and three duct of third duct work at the same time pattern diagram.

Specific embodiment

As shown in Figure 1, a kind of fanjet with the autonomous regulating power of bypass ratio, including the first valve 1, fan 3, Retarder 4, the second valve 6, compressor 7, combustion chamber 11, high-pressure turbine 12, low-pressure turbine 13, third valve 16, the 4th valve 17 and the 5th valve 18；The fan 3, which is connected by retarder 4 with low-pressure turbine 13, forms engine low pressure rotor system, The low pressure rotor system is supported in first bearing 19, second bearing 20,3rd bearing 21 and 6th bearing 24；It is described to calm the anger Machine 7 is connected with high-pressure turbine 12 and forms engine high pressure rotor-support-foundation system, and the high pressure rotor system is supported on fourth bearing 22 In 5th bearing 23；First valve 1 is mounted on the front end for containing casing 15 outside second by hinged mode, and described second Valve 6 is mounted on Middle casing 5 by hinged mode, and the third valve 16 is mounted on rear housing by hinged mode On 25, the 4th valve 17 is mounted on the rear end for containing casing 14 outside first by hinged mode, and the 5th valve 18 is logical It crosses hinged mode and is mounted on the rear end for containing casing 15 outside second；First bearing 19, second bearing 20,3rd bearing the 21, the 4th Bearing 22,5th bearing 23 and 6th bearing 24 are magnetic bearing, and wherein first bearing 19 is mounted on front housing 2；Second Bearing 20,3rd bearing 21 and fourth bearing 22 are mounted on Middle casing 5；5th bearing 23 is intershaft bearing, is mounted on height It presses between rotor-support-foundation system and low pressure rotor system；6th bearing 24 is mounted on rear housing 25.

Embodiment one: as shown in Fig. 2, when aircraft is in underloading or low cruise, engine only needs provide satisfaction The lesser thrust of basic demand, at this moment the first valve 1 and the second valve 6 are closed, and the second duct 9 and third duct 10 are not Thrust is generated, the thrust of engine is only from the first duct 8, and engine transitions erupt dynamic at a whirlpool without outer culvert at this time Machine devises a retarder 4 to give full play to the advantage of component between fan 3 and low-pressure turbine 13, in not shadow While ringing the normal work of low-pressure turbine 13, the blade tip tangential velocity of fan 3 is reduced, but since fan 3 is effective radially Working depth reduces, and 3, fan have played a part of effect, in addition, in order to better meet requirement, in the first duct 8 Secondary Control can also be carried out to thrust by third valve 16 under single duct operating mode.

Embodiment two: as shown in Figure 3 and Figure 4, when aircraft needs medium thrust, engine can be specific according to what is used It is required that closing the first valve 1 or the second valve 6,9 pairs of duct operating modes of the first duct 8 and the second duct or the first culvert are opened The 10 pairs of duct operating modes in road 8 and third duct, the operating mode of the first duct 8 is constant at this time, generates a part of engine Thrust, another part thrust are generated by the air for entering the second duct 9 or third duct 10；It is wanted to better meet use It asks, devises the 4th valve 17 and the 5th valve 18 and the thrust of the second duct 9 and third duct 10 is carried out further respectively It adjusts.

Embodiment three: as shown in figure 5, when aircraft needs high thrust, engine opens three duct operating modes, at this time First valve 1 and the second valve 6 open simultaneously, and fan 3 is in complete working condition, and outside air enters the first duct simultaneously 8, the second duct 9 and third duct 10, three ducts all generate thrust, require to better meet, in the work of three ducts Meanwhile third valve 16, the 4th valve 17 and the 5th valve 18 can be used to carry out adjusting appropriate to engine.

The rotor-support-foundation system of engine uses first bearing 19, second bearing 20,3rd bearing 21, fourth bearing the 22, the 5th The advantages of totally six magnetic bearings support for bearing 23 and 6th bearing 24, this scheme is the vibration that can reduce engine, This bearing also has many advantages, such as that mechanical wear is small, long without lubrication, service life simultaneously, for the engine, due to eliminating one Partial lubrication system simplifies the structure of engine, alleviates the weight of complete machine.

Claims

1. a turbofan engine with bypass ratio self-regulating ability, is characterized in that, comprises the first valve, fan, speed reducer, second valve, compressor, combustion chamber, high pressure turbine, low pressure turbine, the third valve, a fourth valve and a fifth valve; the fan is connected with the low-pressure turbine through the reducer to form a low-pressure rotor system, and the low-pressure rotor system is supported on the first bearing, the second bearing, the third bearing and the sixth bearing; The compressor and the high-pressure turbine are connected to form a high-pressure rotor system, and the high-pressure rotor system is supported on the fourth bearing and the fifth bearing; the first valve is installed at the front end of the second outer casing, and the second valve is installed in the middle On the casing, the third valve is installed on the rear casing, the fourth valve is installed at the rear end of the first outer casing, and the fifth valve is installed at the rear end of the second outer casing.

2. The turbofan engine with the ability to adjust the bypass ratio autonomously according to claim 1, wherein the first valve is mounted on the front end of the second external casing by a hinged manner, and the second valve is hingedly mounted on the front end of the casing. Installed on the intermediate receiver, the third valve is hingedly mounted on the rear receiver, the fourth valve is hingedly mounted on the rear end of the first outer receiver, and the fifth valve is hingedly mounted on the first The rear end of the two external receivers.

3. The turbofan engine with bypass ratio self-adjusting capability according to claim 1, wherein the first bearing, the second bearing, the third bearing, the fourth bearing, the fifth bearing and the sixth bearing are all Magnetic bearing.

4. The turbofan engine with bypass ratio self-adjusting capability according to claim 1, wherein the first bearing 19 is installed on the front casing 2; the second bearing 20, the third bearing 21 and the fourth bearing 22 is installed on the intermediate casing 5; the fifth bearing 23 is an intermediate bearing and is installed between the high pressure rotor system and the low pressure rotor system; the sixth bearing 24 is installed on the rear casing 25.