CN109973244A - Self-driven outer duct counter-rotating annular fan blade compression device - Google Patents

Abstract

The invention relates to a device for continuously adjusting the bypass ratio of a turbofan engine, in particular to a device for compressing an outer bypass of a turbofan engine with a counter-rotating fan ring. A self-driven outer duct counter-rotating annular fan blade compression device includes an inner duct of an engine, a duct arranged outside the inner duct is a third outer duct, and an inlet guide vane in the third outer duct and a There are two rows of counter-rotating rotating members between the stator blades, and the two rows of counter-rotating rotating members are respectively an upstream rotating member and a downstream rotating member. on the casing. The invention adopts two rows of counter-rotating fan ring structures, so that the pressure ratio and flow rate of the third outer duct can be effectively reduced under the same conditions as the rotational speed of the rotor structure and the size of the third outer duct, thereby reducing noise and power consumption. As well as the design difficulty, the working range of the turbofan engine is greatly expanded, and the variable cycle advantages of this type of engine are brought into full play.

Description

Self-driven outer duct counter-rotating annular fan blade compression device

technical field

The invention relates to a device for continuously adjusting the bypass ratio of a turbofan engine, in particular to a device for compressing an outer bypass of a turbofan engine with a counter-rotating fan ring.

Background technique

A typical requirement for next generation aviation gas turbofan engines is variable cycle. The variable cycle engine realizes the change of cycle parameters such as boost ratio, flow rate and bypass ratio by changing the geometry, size and position of some components, so that the engine has the best performance under various working conditions, thus affecting the flight of the aircraft. Height and Mach number, etc. have good adaptability.

US Patent No. 4,043,121 to Thomas et al., entitled "Dual Rotor Variable Cycle Engine", discloses an engine with a blade tip fan (Flade) that controls air by adjusting adjustable guide vanes in the external duct of the blade tip fan flow, enabling variability in the engine cycle.

In the US patent US005809772A, a dual-extension variable cycle engine with a core engine driven fan (CDFS) configuration is disclosed. The main difference in structure from the conventional single-ducted turbofan engine is that the fan is divided into front and rear parts. The front fan is driven by the low-pressure turbine shaft, the rear fan is connected to the high-pressure shaft, and the rear fan is driven by the core engine. The fan, the front/rear fans each have an external duct. The engine has an optimal bypass ratio over a wide operating range through the mode selection valve in the rear bypass of the front fan and the adjustable front area injector (VABI) adjustment of the CDFS rear bypass.

In US20100180572A1, a three-extension turbofan engine with CDFS and Flade configurations is disclosed. The tip fan in the third connotation is directly driven by the inner duct fan blades and is arranged at the front end of the engine. Chinese patent CN1619129A discloses an engine with a tail Flade tip fan, wherein the Flade tip fan is connected with a low pressure turbine blade or a free turbine blade, and is arranged at the rear end of the engine. This type of three-connotation turbofan engine is also known as an adaptive cycle engine, or smart engine. The third external bypass is added on the basis of the double external bypass variable cycle engine. This flow path can not only increase the adjustment range of the bypass ratio of the engine, optimize the flow matching between the intake port and the engine, but also be used for thermal management and thermal management of high-energy weapons. Stealth etc.

Because the outer ducted Flade tip fan and the inner ducted blade are directly connected, it brings many disadvantages to the engine design: one is the difficulty of blade strength design, which limits the choice of tangential speed of the blade; the other is that the coupling connection makes the control The system is more complex, and the degree of freedom of adjustment is reduced, which is not conducive to the expansion of the engine's working range; third, the performance of each bypass cannot be taken into account, which greatly limits the multi-pass engine to take advantage of variable cycles.

SUMMARY OF THE INVENTION

The purpose of the present invention is to avoid the deficiencies of the prior art and provide an electromagnetic device with a compact structure, independent control mechanism, mechanical decoupling from the inner channel system, and a large degree of adjustment freedom, which adopts the integrated design of the motor rotor and the counter-rotating fan ring rotor blades. Driven outer duct counter-rotating annular fan blade compression system.

In order to achieve the above purpose, the technical solution adopted in the present invention is: a self-driven outer duct counter-rotating annular fan blade compression device, comprising an inner duct of an engine, and a duct arranged on the outside of the inner duct is a third outer duct. , between the inlet guide vanes and the stator vanes in the third outer duct are provided with two rows of counter-rotating rotating components, the two rows of counter-rotating rotating components are upstream rotating components and downstream rotating components respectively, and the upstream rotating components and downstream rotating components are respectively It is arranged on the ducted casing of the third outer duct through the turntable bearing.

Further, the two rows of counter-rotating rotating members include upstream fan blades and downstream fan blades, and the upstream fan blades and the downstream fan blades are respectively arranged on the inner walls of two annular support frames, and the annular support frames have inner and outer walls, An electromagnetic device is arranged on the outer wall of the annular support frame; the annular support frame is arranged on the outer casing of the third outer duct through a pair of turntable bearings, and the outer casing corresponding to the electromagnetic device is also provided with a motor stator; The magnetic poles of the electromagnetic device and the motor stator are arranged in a circumferential array, and the polarities of the electromagnetic device and the motor stator are opposite. The rotating member composed of the upstream fan blade, the annular support frame, and the electromagnetic device is the upstream rotating member, and the rotating member composed of the downstream fan blade, the annular supporting frame, and the electromagnetic device is the downstream rotating member.

Further, the bearing clearance of the slewing plate bearing is smaller than the blade tip clearance, and the blade tip clearance refers to the clearance between the upstream fan blade and the downstream fan blade and the inner casing of the third outer duct.

Further, the two rows of counter-rotating rotating members include upstream fan blades and downstream fan blades, and the upstream fan blades and the downstream fan blades are respectively arranged on the outer walls of two annular support frames, and the annular support frame has inner and outer walls, An electromagnetic device is arranged on the inner wall of the annular support frame; the annular support frame is arranged on the inner casing of the third outer duct through a pair of turntable bearings, and the inner casing corresponding to the electromagnetic device is also provided with a motor stator, so The magnetic poles of the electromagnetic device and the motor stator are arranged in a circumferential array, and the polarities of the electromagnetic device and the motor stator are opposite. The rotating member composed of the upstream fan blade, the annular support frame, and the electromagnetic device is the upstream rotating member, and the rotating member composed of the downstream fan blade, the annular supporting frame, and the electromagnetic device is the downstream rotating member.

Further, the bearing clearance of the slewing plate bearing is smaller than the blade tip clearance, and the blade tip clearance refers to the clearance between the upstream fan blade and the downstream fan blade and the outer casing of the third outer duct.

Further, the electromagnetic device is a permanent magnet or a motor rotor coil.

Further, the slewing bearing is a cylindrical roller bearing.

Further, the installation angle of the guide vanes is adjusted in cooperation with the two rows of counter-rotating rotating members, so that the upstream blades of the upstream rotating members can obtain the best angle of attack of the incoming flow.

Further, the gap between the counter-rotating rotating member and the casing is provided with grate teeth, and the grate teeth are tightly sealed to reduce air leakage and flow.

Further, the flow rate of the third outer duct varies within the range of 0% to 60% of the flow rate of the whole aircraft; when the flow rate of the third outer duct is 0, the third outer duct is in a closed state, and the aircraft is at supersonic speed at this time. Cruise or maneuver state; when the third connotation flow is 60% of the whole machine flow, the engine is in a state of large bypass ratio, that is, the aircraft is in a subsonic cruise state. In actual flight, the engine can meet the working performance requirements by adjusting the third extrinsic flow.

The beneficial effects of the present invention are: the present invention adopts a two-row counter-rotating fan ring structure, which can effectively reduce the rotational speed of the rotor structure and reduce the third outer bypass channel under the same conditions as the pressure ratio and flow rate of the third outer bypass channel. size, thereby reducing noise, power consumption, and design difficulties. The use of two-row counter-rotating fan ring structure can increase the pressure ratio and flow rate of the third outer duct at the same rotational speed, and make the airflow angle at the outlet of the downstream counter-rotating rotating member closer to the axial direction, effectively reducing the circumferential speed , even the outlet guide vanes can be eliminated.

Different from the traditional outer ducted Flade blade tip fan, the present invention adopts the integrated design of the motor rotor and the counter-rotating fan ring fan blades, forming an outer ducted counter-rotating fan ring compression system driven by a motor independently, and has the advantages of compact structure, The independent control mechanism and the mechanical decoupling of the internal channel system can realize a large-scale continuous adjustment of the engine bypass ratio, effectively optimize the matching between the engine and the intake channel, reduce or even eliminate the overflow resistance, and greatly expand the turbofan engine. The working range is suitable for multi-ducted gas turbofan engines, variable cycle gas turbofan engines, adaptive cycle engines and intelligent engines with high performance requirements, wide working range and multiple working modes, which can give full play to the changes of this type of engine. Cycle advantage.

The invention realizes independent motor drive, so that the control mechanism is independent and has a greater degree of freedom of adjustment; it does not increase the design difficulty of the inner duct blades; Layout optimization. At the same time, a variety of working mode options are realized, which can meet the high-performance requirements of the engine under multiple operating conditions such as subsonic cruise, transonic acceleration and supersonic cruise. In the low-power state of the aircraft such as subsonic cruise, the engine mode selection valve and the front/rear adjustable-area duct ejector are both open, the third outer duct counter-rotating fan ring works at high speed, and the engine operates with a large duct At this time, the propulsion efficiency of the engine is higher and the fuel consumption rate is lower. Under the high-power conditions of aircraft climb, acceleration and supersonic flight, the engine turns off each VABI to promote more air into the core aircraft, and the adaptive cycle engine operates in a thrust priority state.

Description of drawings

1 is a schematic diagram of the overall structure of an adaptive variable cycle engine equipped with the present invention;

Fig. 2 is the front enlarged structural schematic diagram of the overall structure of the engine in Fig. 1;

Fig. 3 is the rear enlarged structural schematic diagram of the overall structure of the engine in Fig. 1;

4 is a schematic structural diagram of Embodiment 1 of the present invention;

5 is a schematic diagram of the composition of the annular support frame, the fan blade and the electromagnetic device in Embodiment 1;

6 is a schematic structural diagram of Embodiment 2 of the present invention;

FIG. 7 is a schematic diagram of the composition structure of the annular support frame, the fan blade and the electromagnetic device in the second embodiment.

Detailed ways

The principles and features of the present invention will be described below with reference to the accompanying drawings. The examples are only used to explain the present invention, but not to limit the scope of the present invention.

Embodiment 1: As shown in Figure 1, Figure 2, Figure 3, Figure 4, Figure 5, a self-driven outer duct annular counter-rotating fan blade compression device, in the rear of the traditional fan 12 is provided with inner, middle, outer Three flow channels, the inner flow channel is communicated with the core engine drive fan 13, the middle flow channel is communicated with the entrance of the second outer duct 14, the outer flow channel is communicated with the inlet of the first outer duct 8, and the second outer duct is communicated with the inlet of the first outer duct 8. The outlet of the duct 14 is communicated with the first outer duct 8 through the front variable area duct ejector 9, and a mode selection valve 6 is also provided at the entrance of the first outer duct 8; the core engine drives the fan The rear part of 13 is the inner and outer annular flow channels, the inner annular flow channel is communicated with the high-pressure compressor 15, and the middle annular flow channel is communicated with the second outer duct 14. The rear part of the engine 15 is connected with a combustion chamber 10, a high-pressure turbine 16, and a low-pressure turbine 17 in sequence; at the exit of the second outer bypass 14, that is, the rear of the engine, there are two inner and outer flow channels, and the inner flow The variable area bypass ejector 11 communicates with the outlet of the inner channel after the channel passes through, and the outer channel communicates with the outlet of the third outer channel 7 . The third outer duct 7 is arranged on the outside of the inner duct, and between the inlet guide vanes 1 and the stator vanes 5 in the third outer duct 7 are provided with two rows of counter-rotating rotating members, and the two rows of counter-rotating rotating members They are an upstream rotating member and a downstream rotating member respectively, and the upstream rotating member and the downstream rotating member are respectively disposed on the bypass casing of the third outer bypass 7 through the slewing plate bearing 20 .

The two rows of counter-rotating rotating members include upstream fan blades 4 and downstream fan blades 21. The upstream fan blades 4 and the downstream fan blades 21 are respectively arranged on the inner walls of the two annular support frames 18, and the annular support frames 18 have inner blades. , the outer wall, an electromagnetic device 19 is arranged on the outer wall of the annular support frame 18; the annular support frame is arranged on the outer casing of the third outer duct 7 through a pair of turntable bearings, and the outer casing corresponding to the electromagnetic device is also A motor stator 3 is provided; the magnetic poles of the electromagnetic device 19 and the motor stator 3 are arranged in a circumferential array, and the electromagnetic device 19 and the motor stator 3 have opposite polarities. The electromagnetic device 19 is a permanent magnet or a motor rotor coil. The bearing clearance of the slewing plate bearing 20 is smaller than the blade tip clearance, and the blade tip clearance refers to the inner casing clearance between the upstream fan blade 4 and the downstream fan blade 21 and the third outer duct 7 . The said guide vane 1 cooperates with the two rows of counter-rotating rotating members to adjust the installation angle, so that the upstream fan blades 4 of the upstream rotating member can obtain the best incoming flow angle of attack.

The gap between the counter-rotating rotating member and the casing is provided with grate teeth, and the grate teeth are tightly sealed to reduce air leakage and flow. The flow of the third outer duct 7 varies within the range of 0 to 60% of the flow of the whole aircraft; when the third outer flow is 0, the third outer duct is in a closed state, and the aircraft is in supersonic cruise or The maneuvering state is the same as the existing double bypass engine working state; when the third external flow is 60% of the whole machine flow, the engine is in a state with a large bypass ratio, that is, the aircraft is in a subsonic cruise state. In actual flight, the engine can meet the working performance requirements by adjusting the third extrinsic flow.

Example 2: As shown in Figures 6 and 7, it is the same as Example 1, except that the two rows of counter-rotating rotating components include upstream fan blades 4 and downstream fan blades 21, upstream fan blades 4 and downstream fan blades The leaves 21 are respectively arranged on the outer walls of the two annular support frames 18 , the annular support frames 18 have inner and outer walls, and an electromagnetic device 19 is arranged on the inner wall of the annular support frame 18 ; On the inner casing of the third outer duct 7, the inner casing corresponding to the electromagnetic device is also provided with a motor stator 3, and the magnetic poles of the electromagnetic device 19 and the motor stator 3 are arranged in a circumferential array, The electromagnetic device 19 is of opposite polarity to the motor stator 3 . The bearing clearance of the slewing plate bearing is smaller than the blade tip clearance, and the blade tip clearance refers to the outer casing clearance between the fan blade 4 and the third outer duct 7 .

The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection of the present invention. within the range.

Claims (10)

1. a kind of by-pass air duct of driving certainly is to change shape flabellum compression set, which is characterized in that the main duct including engine, setting Duct on the outside of the main duct is third by-pass air duct, in the inlet guide vane in third by-pass air duct and between stator blade Equipped with two rows to rotating member is turned, two rows of is respectively upstream rotating member and downstream rotating member, upstream rotation to rotating member is turned Turn component and downstream rotating member passes through turntable bearing respectively and is arranged on the duct casing of third by-pass air duct.

2. the by-pass air duct of driving certainly as described in claim 1 is to change shape flabellum compression set, which is characterized in that the two rows It include upstream flabellum and downstream flabellum to rotating member is turned, upstream flabellum and downstream flabellum are separately positioned on two ring holders On inner wall, the ring holder has inside and outside wall, and calutron is equipped on ring holder outer wall；Ring holder It is arranged on the outer casing of third by-pass air duct by a pair of of turntable bearing, is additionally provided on outer casing corresponding with the calutron Motor stator；The magnetic pole of the calutron and motor stator circumferentially array arrangement, the pole of calutron and motor stator Property is opposite.

3. the by-pass air duct of driving certainly as claimed in claim 2 is to change shape flabellum compression set, which is characterized in that the turntable The bearing clearance of bearing is less than tip clearance, and tip clearance refers between upstream flabellum and downstream flabellum and the interior casing of third by-pass air duct Gap.

4. the by-pass air duct of driving certainly as described in claim 1 is to change shape flabellum compression set, which is characterized in that the two rows It include upstream flabellum and downstream flabellum to rotating member is turned, upstream flabellum and downstream flabellum are separately positioned on two ring holders On outer wall, the ring holder has inside and outside wall, and calutron is equipped on ring holder inner wall；Ring holder It is arranged on the interior casing of third by-pass air duct by a pair of of turntable bearing, is additionally provided on interior casing corresponding with the calutron Motor stator, the magnetic pole of the calutron and motor stator circumferentially array arrangement, the pole of calutron and motor stator Property is opposite.

5. the by-pass air duct of driving certainly as claimed in claim 4 is to change shape flabellum compression set, which is characterized in that the turntable The bearing clearance of bearing is less than tip clearance, and tip clearance refers between upstream flabellum and downstream flabellum and the outer casing of third by-pass air duct Gap.

6. the by-pass air duct of driving certainly as described in claim 2 to 5 is any is to change shape flabellum compression set, which is characterized in that institute The calutron stated is permanent magnet or motor-spin-coil.

7. the by-pass air duct of driving certainly as described in claim 2 to 5 is any is to change shape flabellum compression set, which is characterized in that institute The turntable bearing stated is cylinder roller bearing.

8. the by-pass air duct of driving certainly as described in claim 2 to 5 is any is to change shape flabellum compression set, which is characterized in that institute The guide vane cooperation stated is two rows of to the progress setting angle adjustment of rotating member revolving speed is turned, and makes the upstream of the upstream rotating member Flabellum obtains the optimal incoming flow angle of attack.

9. it is as described in claim 1 from driving by-pass air duct to change shape flabellum compression set, which is characterized in that it is described to turning Gap between rotating member and casing is equipped with comb tooth, and labyrinth gas seals reduce air leakage flow.

10. the by-pass air duct of driving certainly as described in claim 1,2,3,4,5,9 is any is to change shape flabellum compression set, feature It is, the flow of the third by-pass air duct changes in the range of 0~60% complete machine flow；Containing flow outside the third is 0 When, third is contained outside to be in close state, and aircraft is in supersonic cruising or maneuvering condition at this time；It is 60% when containing flow outside third When complete machine flow, engine is in the state of big bypass ratio, i.e. aircraft is in subsonics cruising condition.