CN116398464A - Deformed fan for aviation turbofan engine and optimization method - Google Patents

Deformed fan for aviation turbofan engine and optimization method Download PDF

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Publication number
CN116398464A
CN116398464A CN202310063107.XA CN202310063107A CN116398464A CN 116398464 A CN116398464 A CN 116398464A CN 202310063107 A CN202310063107 A CN 202310063107A CN 116398464 A CN116398464 A CN 116398464A
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China
Prior art keywords
blade
deformation
tail
blades
fan
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Inventor
孙士珺
李晓龙
张英刚
王骥翔
黄叶红
马奕然
李心唱
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Beijing Institute of Technology BIT
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Beijing Institute of Technology BIT
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/002—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by varying geometry within the pumps, e.g. by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a deformation fan for an aviation turbofan engine and an optimization method, and belongs to the field of aviation engines. The invention comprises a blade, a hub and a casing. The blades, the hubs and the casing are formed by laminated structures consisting of carbon fibers and piezoelectric materials, the electrodes drive the piezoelectric materials to drive the whole laminated structure to generate micro deformation required by the blades, the hubs and the casing, and the layout optimization of the piezoelectric materials is used for realizing the high-precision micro deformation of the three layers of the local part, the array and the whole part of the deformed fan; the wider adjustment capability of the bending angle, the inlet attack angle and the outlet airflow angle is realized through the quick response and the large-scale deformation of the three-section variable camber blade; through fusing the advantages of large deflection variable blades based on mechanical structure driving and high deformation precision of intelligent piezoelectric material driving blades, the precise regulation and control of blade channel vortexes and shock waves are realized, flow separation is weakened, and the efficiency and stability of the deformation fan for the aviation turbofan engine are improved under wide incoming flow Mach number and wide folding rotating speed.

Description

Deformed fan for aviation turbofan engine and optimization method
Technical Field
The invention belongs to the technical field of aeroengines, and particularly relates to a high-precision and quick-response controllable deformation fan and an optimization method.
Background
Future advanced aeroengine fans need to meet the requirements of high aerodynamic performance and wide working margin in a wide speed range, a large airspace and a wide folding rotational speed range. In the prior art, an adjustable static/guide vane technology is generally adopted, namely, the blades rotate around the shaft to change the installation angle to adjust the outlet airflow angle, so that the requirements of the rear row of blades on the inlet airflow direction are met, and the stable working margin is widened. However, when the static/vane mounting angle adjustment amplitude is large, the attack angle is increased, which results in a large total pressure loss of the static/vane itself and damages the uniformity and stability of the intake air flow. Further, as a special example of the adjustable blade, namely the camber-changing blade, the outlet air flow angle adjusting range of the adjustable blade can be effectively widened, the self loss is greatly reduced, and the adjustable blade has the advantage of large deformation of single actuation. But has two disadvantages: a) Gaps exist in the fixed and rotating parts of the camber-changing blades, and larger loss can be induced under the condition of large rotation angle of the rear blade; b) The rotation of the rear blade is difficult to ensure that the suction pressure surface is continuous and smooth, so that flow separation happens prematurely, and the pneumatic performance is reduced.
Disclosure of Invention
In order to solve the defects of the traditional mechanical variable camber blade, the main purpose of the invention is to provide a deformation fan for an aviation turbofan engine and an optimization method, wherein the blade, the hub and the casing are all composed of laminated structures composed of carbon fibers and piezoelectric materials, the electrode drives the piezoelectric materials to drive the whole laminated structure to generate micro deformation required by the blade, the hub and the casing, and the layout optimization of the piezoelectric materials is used for realizing the high-precision micro deformation of three layers of local, array and whole of the deformation fan; the wider adjustment capability of the bending angle, the inlet attack angle and the outlet airflow angle is realized through the quick response and the large-scale deformation of the three-section variable camber blade; in addition, through fusing the advantages of large deflection blade deflection based on mechanical structure driving and high deformation precision of the intelligent piezoelectric material driving blade, the precise regulation and control of blade channel vortex and shock waves are realized, flow separation is further weakened, and the efficiency and stability of the deformation fan for the aviation turbofan engine are improved under wide incoming flow Mach number and wide folding rotating speed.
In order to achieve the first object disclosed by the invention, the following technical scheme is adopted:
the invention discloses a deformation fan for an aviation turbofan engine, which comprises blades, a hub and a casing. The blade, the hub and the casing are all composed of laminated structures composed of carbon fibers and piezoelectric materials. In the laminated structure, the piezoelectric material and the driving electrode are wrapped with carbon fibers. The electrode drives the piezoelectric material to drive the whole laminated structure to generate micro deformation required by the blade, the hub and the casing, and the layout optimization of the piezoelectric material realizes the high-precision micro deformation of the three layers of the local, the array and the whole of the deformed fan. The blade micro-deformation cannot meet the requirements of a variable cycle engine or a turbine punching combined engine on efficient and stable work in a wide speed range and a large airspace, and adopts a three-section variable camber blade configuration driven by a mechanical structure, wherein the three-section variable camber configuration is based on a multi-hinge connection mechanical structure driven by a motor, and drives a front blade and a tail blade to rotate around a shaft, so that the rapid response and large-scale deformation of the three-section blade configuration of the front blade, the middle blade and the tail blade are realized, and further, the wider adjustment capability on a camber angle, an air inlet attack angle and an outlet airflow angle is realized; on the basis of quick response and large-scale deformation, in order to further solve the problem that the three-section type deflection blade configuration has discontinuous smoothness of a blade surface during rotation, because the laminated structure of the blade adopts intelligent piezoelectric fiber composite materials, high-precision micro deformation of the three-section type deflection blade configuration is realized through voltage change applied to a driving electrode, namely the three-section type deflection blade configuration realizes accurate regulation and control on vortex and shock waves of a blade channel by fusing the advantages of large deflection of the deflection blade driven by a mechanical structure and high deformation precision of the intelligent piezoelectric material, further weakens flow separation, and improves the efficiency and stability of a deformation fan for an aviation turbofan engine under wide incoming flow Mach number and wide folding rotating speed.
The blades are divided into rotor blades and stator blades.
The invention discloses a working method of a deformed fan for an aviation turbofan engine, which comprises the following steps:
under low folding rotation speed or low-speed cruising, the variable camber blades are driven to rotate around the shaft by a motor, and the installation angles of the front blades, the rear blades and the front and rear blades of the variable camber stator are respectively increased, so that the air inlet attack angle of the rotor blade is reduced. Further, aiming at the fan supercharging ratio adjusting requirement, the total supercharging ratio is improved by reducing the work load of the rotor tail blade along the anticlockwise rotation angle beta, and meanwhile, the static pressure ratio is improved by increasing the clockwise rotation angle gamma of the stator front blade and reducing the clockwise rotation angle delta of the stator tail blade; the work load is reduced by increasing the rotation angle beta of the rotor tail vane along the anticlockwise direction, the total supercharging ratio is reduced, and the static pressure ratio is reduced by reducing the rotation angle gamma of the stator front vane along the clockwise direction and increasing the rotation angle delta of the stator tail vane along the clockwise direction. On the other hand, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness and height chord length of the blade are regulated, smooth transition of the front blade, the tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is increased, the clearance between the blade tops is reduced, and the thrust of the engine under low-speed cruising is improved.
Under the condition of high folding rotational speed or high-speed cruising, the motor drives the variable camber blades to rotate around the shaft, so that the installation angles of the front blades and the tail blades of the variable camber rotor and the front blades and the tail blades of the variable camber stator are respectively reduced, and the air inlet attack angle of the rotating stationary blade is reduced. Further, aiming at the fan pressure ratio regulation requirement, the total pressure ratio is increased by increasing the work amount along the clockwise rotation angle beta of the rotor tail blade, and the static pressure ratio is increased by reducing the counter-clockwise rotation angle gamma of the stator front blade and increasing the counter-clockwise rotation angle delta of the stator tail blade; the work load is reduced by reducing the rotor tail vane rotation angle beta clockwise, the total supercharging ratio is reduced, and the static pressure ratio is reduced by increasing the stator front vane rotation angle gamma anticlockwise and reducing the stator tail vane rotation angle delta anticlockwise. On the other hand, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness, height, chord length and the like of the blade are regulated, smooth transition of the front/tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is regulated, and the clearance between the blade tops is reduced, so that the thrust of the engine under high-speed cruising is regulated.
The invention also discloses a method for optimizing the deformed fan for the aviation turbofan engine, which is used for optimizing the deformed fan for the aviation turbofan engine. The deformation fan optimization method for the aviation turbofan engine comprises the following steps of:
a) Determining the incoming flow speed of an engine according to the cruising speed of the aircraft, and rotating the front She Rao shaft and the tail She Rao shaft of the camber-changing rotor blade towards the increasing direction of the mounting angle when the incoming flow speed or the reduced rotating speed is lower than a design value; when the incoming flow speed or the folding rotational speed is higher than the design value, the front and the tail She Rao shafts of the camber turning stator blades rotate towards the direction of decreasing the installation angle. Determining the relative speed direction of the air inlet according to the axial incoming flow speed and the reduced rotating speed, combining a speed triangle, further determining the rotating angle of the front blade of the rotor by combining the attack angle loss characteristic, and simultaneously determining the rotating angle of the tail blade of the rotor by combining the total supercharging ratio requirement; and determining the rotation angle of the front blade of the stator blade according to the attack angle loss characteristic of the stator blade and the absolute airflow angle of the rotor outlet, and determining the rotation angle of the rear blade of the stator according to the static pressure ratio and the airflow direction requirement of the outlet.
b) According to the mechanical characteristics and piezoelectric driving deformation characteristics of the carbon fiber/piezoelectric material laminated structure, the typical section blade profile and blade height aerodynamic force and centrifugal force deformation characteristics of the three-dimensional blade are obtained, and the coupling deformation characteristics under the action of the carbon fiber/piezoelectric material laminated structure with certain voltage and position layout are obtained.
c) Based on the step b), the three-section deflection blade adopting the carbon fiber/piezoelectric material laminated structure is obtained, the stressed deformation characteristics under the two working conditions in the step a) are combined, the deformation characteristics of the blade shape, the front tail blade/middle blade gap under the coupling action of aerodynamic force, centrifugal force and piezoelectric drive are obtained, and the pneumatic loss and the pressure ratio characteristic of the deformation fan are obtained through a numerical simulation tool. Comparing the simulation result with an optimization target, and if the performance does not meet the requirement, adjusting the rotation angle of the front and rear blades of the rotor blade in the step a) and the layout of the piezoelectric material in the step b), and performing cyclic iteration until the pneumatic performance meets the index requirement, so as to realize the optimization of the deformed fan for the aviation turbofan engine.
Through layout optimization of piezoelectric materials, high-precision micro-deformation of three layers of parts, arrays and whole of the deformed fan is realized, and the realization method is as follows:
step (1): the piezoelectric material is integrally wrapped on the surface of the blade, so that the integral adjustment of the thickness, the bending degree, the angle, the curvature, the height and the chord length of the blade is realized, and the integral adjustment with relatively large adjustment quantity and wide coverage range is realized.
Step (2): through arranging piezoelectric material in blade passageway part, control blade/passageway dihedral angle, blade local curvature, fore-aft leaf/middle leaf clearance gap or top of the blade clearance, realize adjusting regional accurate, the little accurate regulation of coverage. The blade channel comprises locally a casing, an end wall or a suction surface corner region.
Step (3): through arranging the piezoelectric material array at the blade passageway, have the regulation advantage that regulation region is accurate, coverage is great concurrently.
On the basis of realizing the adjustment of the steps (1), 2) and (3), the precise regulation and control of the vortex and shock waves of the blade channel are realized by fusing the advantages of large deformation amount of the variable camber blade driven by a mechanical structure and high deformation precision of the blade driven by an intelligent piezoelectric material, so that the flow separation is further weakened, and the efficiency and stability of the deformation fan for the aviation turbofan engine are improved under the conditions of wide incoming flow Mach number and wide folding rotational speed.
The beneficial effects are that:
1. the invention discloses a deformation fan for an aviation turbofan engine and an optimization method, wherein a mechanical structure three-section type deflection blade and an intelligent piezoelectric fiber deformation blade are combined, the advantages of the mechanical structure three-section type deflection blade and the intelligent piezoelectric fiber deformation blade are fully utilized, the large deformation of the blade is realized by virtue of the mechanical structure type deflection blade, and the tiny and precise deformation is realized by virtue of the intelligent piezoelectric fiber material. Meanwhile, the problem of discontinuous and smooth blade surface when the traditional mechanical deflection blade rotates can be avoided by sticking an intelligent piezoelectric material on the surface of the blade or directly adopting a carbon fiber/piezoelectric lamination structure.
2. According to the deformation fan and the optimization method for the aviation turbofan engine, disclosed by the invention, the rapid adjustment of the inlet attack angle and the outlet airflow angle is realized through the deflection structure, so that the reorganization of shock wave and vortex structures is realized, and the fan is ensured to stably work in a wide incoming flow Mach number and rotating speed range. Meanwhile, the piezoelectric material drives the carbon fiber/piezoelectric lamination structure blade to generate local, array and integral high-precision micro-deformation, so that the regulation and control of shock wave, vortex and separation key flow structures are realized, the flow separation is further weakened, and the efficient operation of the fan is ensured.
3. The invention discloses a deformed fan for an aviation turbofan engine and an optimization method thereof, which are divided into two working modes of low-folding-speed or low-speed cruising, high-folding-speed or high-speed cruising according to cruising speed and folding-speed of the deformed fan for the aviation turbofan engine. On one hand, under the low folding rotation speed or low-speed cruising, the inlet attack angle is reduced by increasing the installation angle of the front blade of the camber-changing rotor stator, so that the flow separation is weakened, and the aerodynamic loss is reduced; on the other hand, according to the requirement of the supercharging ratio, the total pressure ratio and the static pressure ratio of the fan are respectively adjusted by adjusting the rotation and the stator tail blade installation angle. In addition, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness and height chord length of the blade are regulated, smooth transition of the front blade, the tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is increased, the clearance between the blade tops is reduced, and the efficiency of the engine under low-speed cruising is improved.
On one hand, under the condition of high folding rotation speed or high-speed cruising, the inlet attack angle is reduced by reducing the installation angle of the front blade of the camber-changing rotor stator, so that the flow separation is weakened, and the aerodynamic loss is reduced; on the other hand, according to the requirement of the supercharging ratio, the total pressure ratio and the static pressure ratio of the fan are respectively adjusted by adjusting the rotation and the stator tail blade installation angle. In addition, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness, height, chord length and the like of the blade are regulated, smooth transition of the front/tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is regulated, the clearance between the blade tops is reduced, and the engine efficiency under high-speed cruising is improved.
Drawings
Fig. 1 is a schematic view of a radial structure of a deformed fan for an aviation turbofan engine.
Fig. 2 is a schematic view of a deformed fan B2B section blade profile for an aviation turbofan engine according to the present invention.
Wherein: 10-front She Feng tract, 5-tail lobe rotation axis, 7-piezoelectric material structure, alpha-front She Zhuaijiao, beta-tail She Zhuaijiao, b 1 -front She Zhouxiang chord length, b 2 -middle leaf axial chord length, b 3 Tail She Zhouxiang chord length.
Fig. 3 is a schematic diagram showing the adjustment of the front and rear blade rotation of a rotor with a section B2B in a low-folding rotation speed or low-speed cruising mode of a deformed fan for an aviation turbofan engine, wherein fig. 3 (a) shows a high-precision, fast-response and controllable deformed fan rotor in a low-folding rotation speed or low-speed cruising mode, and fig. 3 (B) shows a high-precision, fast-response and controllable deformed fan stator in a low-folding rotation speed or low-speed cruising mode.
Fig. 4 is a schematic diagram showing the adjustment of the front and rear blade rotation of a rotor with a section B2B in a high-speed folded rotation speed or high-speed cruising mode of a deformed fan for an aviation turbofan engine, wherein fig. 4 (a) shows a high-precision, fast-response and controllable deformed fan rotor in a high-speed folded rotation speed or high-speed cruising mode, and fig. 4 (B) shows a high-precision, fast-response and controllable deformed fan stator in a high-speed folded rotation speed or high-speed cruising mode.
FIG. 5 is a schematic cross-sectional view of an array-distributed piezoelectric driven deformation structure hollow fan blade of the present invention.
Wherein: 1-deflection rotor front blade, 2-deflection rotor middle blade, 3-deflection rotor tail blade, 4-front blade rotation shaft, 5-tail blade rotation shaft, 6-deflection stator, 7-local distribution carbon fiber/piezoelectric material laminated structure, 8-array distribution carbon fiber/piezoelectric laminated structure, 9-integral distribution carbon fiber/piezoelectric laminated structure, 10-front blade/middle blade slot, 11-deflection stator front blade, 12-deflection stator tail blade and 13-deflection stator tail blade.
FIG. 6 is a flow chart of a deformable fan optimization with high accuracy, fast response, large scale deformation features of the present invention.
Detailed Description
For a better description of the objects and advantages of the present invention, the following description will be given with reference to the accompanying drawings and examples.
Example 1:
as shown in fig. 1 to 5, the present embodiment discloses a deformation fan for an aviation turbofan engine, which comprises a camber rotor front blade 1, a camber rotor middle blade 2, a camber rotor tail blade 3, a front blade rotating shaft 4, a tail blade rotating shaft 5, a camber stator 6, a locally distributed carbon fiber/piezoelectric material laminated structure 7, an array distributed carbon fiber/piezoelectric laminated structure 8, an integrally distributed carbon fiber/piezoelectric laminated structure 9, a front blade/middle blade slit channel 10, a camber stator front blade 11, a camber stator tail blade 13 and a camber stator tail blade 13.
The deformed fan rotor stator is a three-section variable camber blade, and the front blade 1 and the tail blade 3 of the deformed fan rotor stator can rotate around the shafts 4 and 5 respectively, as shown in fig. 1, the geometric angle and camber of the inlet of the blade can be quickly and largely adjusted, so that the purposes of reducing attack angles under non-design working conditions and adjusting the supercharging ratio in a wide range are achieved. The blade material is a carbon fiber/piezoelectric laminated structure, and according to practical requirements, the blade material can be arranged into a local distribution carbon fiber/piezoelectric material laminated structure 7 or an array distribution carbon fiber/piezoelectric material laminated structure 8 or an overall distribution carbon fiber/piezoelectric material laminated structure 9, and as shown in fig. 1, the electrode voltage is adjusted, so that the piezoelectric material is driven to generate required high-precision deformation: on one hand, the method can be used for changing the thickness and the curvature of the blade profile so as to regulate and control the loss of the blade profile; on the other hand, the clearance between the tip of the rotor and the stator of the adjustable vane and the clearance between the seam 10 between the front tail vane 1 and the middle vane 2 of the variable camber are reduced, as shown in fig. 2, so that leakage loss is reduced.
The working method of the deformation fan for the aviation turbofan engine disclosed by the embodiment comprises the following steps:
as shown in fig. 3, at low folding rotational speed or low-speed cruising, the motor drives the camber blades to rotate around the shaft, so that the mounting angles of the front blade 1, the tail blade 3 and the front blade 11 and the tail blade 13 of the camber rotor are respectively increased, and the air inlet attack angle of the rotating stator blade is reduced. Further, aiming at the fan boost ratio adjustment requirement, the total boost ratio is increased by reducing the work load of the rotor tail vane 3 along the anticlockwise rotation angle beta, and the static pressure ratio is increased by increasing the stator front vane 11 along the clockwise rotation angle gamma and reducing the stator tail vane 13 along the clockwise rotation angle delta; the amount of work is reduced by increasing the rotor tail vane 3 along the counterclockwise rotation angle beta, the total supercharging ratio is reduced, and the static pressure ratio is reduced by decreasing the stator front vane 11 along the clockwise rotation angle gamma, and increasing the stator tail vane 13 along the clockwise rotation angle delta. On the other hand, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness and height chord length of the blade are regulated, the smooth transition of the front/tail blade and the middle blade is ensured, the gap between the seam is reduced, and the leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is increased, the clearance between the blade tops is reduced, and the thrust of the engine under low-speed cruising is improved.
The other working method of the controllable deformation fan with the characteristics of high precision, quick response and large-scale deformation disclosed by the embodiment is as follows:
as shown in fig. 4, at high folding rotational speed or high-speed cruising, the motor drives the camber blades to rotate around the shaft, so that the mounting angles of the front blade 1, the tail blade 3 and the front blade 11 and the tail blade 13 of the camber rotor are respectively reduced, and the air inlet attack angle of the rotating stator blade is reduced. Further, aiming at the fan pressure ratio regulation requirement, the total pressure ratio is increased by increasing the work amount of the rotor tail vane 3 along the clockwise rotation angle beta, and the static pressure ratio is increased by reducing the stator front vane 11 along the anticlockwise rotation angle gamma and increasing the stator tail vane 13 along the anticlockwise rotation angle delta; the amount of work is reduced by reducing the rotor tail vane 3 along the clockwise rotation angle beta, the total supercharging ratio is reduced, and the static pressure ratio is reduced by increasing the stator front vane 11 along the counterclockwise rotation angle gamma, and reducing the stator tail vane 13 along the counterclockwise rotation angle delta. On the other hand, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness, height, chord length and the like of the blade are regulated, smooth transition of the front/tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is regulated, and the clearance between the blade tops is reduced, so that the thrust of the engine under high-speed cruising is regulated.
The embodiment also discloses a method for optimizing the deformed fan for the aviation turbofan engine, which is used for optimizing the deformed fan for the aviation turbofan engine. The method for optimizing the deformed fan for the aviation turbofan engine, as shown in fig. 6, comprises the following steps:
a) Determining the incoming flow speed of an engine according to the cruising speed of the aircraft, and rotating the front blades 1 and 11 and the tail blades 3 and 13 of the camber-changing rotor blades around the shaft towards the increasing direction of the installation angle when the incoming flow speed or the reduced rotating speed is lower than a design value; when the incoming flow speed or the reduced rotational speed is higher than the design value, the camber rotor blades leading blades 1 and 11, and trailing blades 3 and 13 are rotated around the shaft in the direction of decreasing the mounting angle. Determining the relative speed direction of the air inlet according to the axial incoming flow speed and the reduced rotating speed, combining a speed triangle, further determining the rotating angle of the front rotor blade 1 by combining the attack angle loss characteristic, and simultaneously determining the rotating angle of the rear rotor blade 3 by combining the total supercharging ratio requirement; the rotation angle of the front blade 11 of the stator blade is determined according to the attack angle loss characteristic of the stator blade and the absolute airflow angle of the rotor outlet, and the rotation angle of the rear blade 13 of the stator is determined according to the static pressure ratio and the airflow direction requirement of the outlet.
b) According to the mechanical characteristics and piezoelectric driving deformation characteristics of the carbon fiber/piezoelectric material laminated structure, the typical section blade profile and blade height aerodynamic force and centrifugal force deformation characteristics of the three-dimensional blade are obtained, and the coupling deformation characteristics under the action of the carbon fiber/piezoelectric material laminated structure with certain voltage and position layout are obtained.
c) Based on the step b), the three-section deflection blade adopting the carbon fiber/piezoelectric material laminated structure is obtained, the deformation characteristics of the blade shape, the rotor front blades 1 and 11, the rotor tail blades 3 and 13/the middle blades 2 and 12 under the coupling action of aerodynamic force, centrifugal force and piezoelectric driving are obtained by combining the stress deformation characteristics under the two working conditions in the step a), and the pneumatic loss and the pressure ratio characteristics of the deformation fan are obtained through a numerical simulation tool. Comparing the simulation result with an optimization target, if the performance does not meet the requirement, adjusting the rotation angles of the front and rear blades 1, 3, 11 and 13 of the rotor stator blades in the step a) and the layout of the piezoelectric materials 7, 8 and 9 in the step b), and performing cyclic iteration until the aerodynamic performance meets the index requirement, namely, optimizing the deformation fan for the aviation turbofan engine.
Through layout optimization of piezoelectric materials, high-precision micro-deformation of three layers of parts, arrays and whole of the deformed fan is realized, and the realization method is as follows:
step (1): the piezoelectric material is integrally wrapped on the surface of the blade, so that the integral adjustment of the thickness, the bending degree, the angle, the curvature, the height and the chord length of the blade is realized, and the integral adjustment with relatively large adjustment quantity and wide coverage range is realized.
Step (2): by arranging the piezoelectric material at the local part of the blade channel, the dihedral angle of the blade/channel, the local curvature of the blade, and the gap between the front and rear blades 1, 3, 11 and 13/the middle blades 2 and 12 or the gap between the blade tops are controlled, so that the precise adjustment of the adjustment area and the precise adjustment with small coverage range are realized. The blade channel comprises locally a casing, an end wall or a suction surface corner region.
Step (3): through arranging the piezoelectric material array at the blade passageway, have the regulation advantage that regulation region is accurate, coverage is great concurrently.
On the basis of realizing the adjustment of the steps (1), 2) and (3), the precise regulation and control of the vortex and shock waves of the blade channel are realized by fusing the advantages of large deformation amount of the variable camber blade driven by a mechanical structure and high deformation precision of the blade driven by an intelligent piezoelectric material, so that the flow separation is further weakened, and the efficiency and stability of the deformation fan for the aviation turbofan engine are improved under the conditions of wide incoming flow Mach number and wide folding rotational speed.
While the foregoing is directed to embodiments of the present invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof, and the scope thereof is determined by the claims that follow.

Claims (4)

1. The utility model provides a deformation fan for aviation turbofan engine which characterized in that: comprises a blade, a hub and a casing; the blade, the hub and the casing are all composed of laminated structures composed of carbon fibers and piezoelectric materials; in the laminated structure, the carbon fiber wraps the piezoelectric material and the driving electrode; the electrode drives the piezoelectric material to drive the whole laminated structure to generate micro deformation required by the blade, the hub and the casing, and the layout optimization of the piezoelectric material realizes the high-precision micro deformation of three layers of local, array and whole of the deformed fan; the blade micro-deformation cannot meet the requirements of a variable cycle engine or a turbine punching combined engine on efficient and stable work in a wide speed range and a large airspace, and adopts a three-section variable camber blade configuration driven by a mechanical structure, wherein the three-section variable camber configuration is based on a multi-hinge connection mechanical structure driven by a motor, and drives a front blade and a tail blade to rotate around a shaft, so that the rapid response and large-scale deformation of the three-section blade configuration of the front blade, the middle blade and the tail blade are realized, and further, the wider adjustment capability on a camber angle, an air inlet attack angle and an outlet airflow angle is realized; on the basis of quick response and large-scale deformation, in order to further solve the problem that the three-section type variable camber blade configuration has discontinuous and smooth blade surfaces when rotating, the laminated structure of the blades adopts intelligent piezoelectric fiber composite materials, and high-precision micro deformation of the three-section type variable camber blade configuration is realized through voltage change applied to a driving electrode, namely the three-section type variable camber blade configuration realizes accurate regulation and control on blade channel vortex and shock waves by fusing the advantages of large variable camber blade deformation quantity driven by a mechanical structure and high deformation precision of the intelligent piezoelectric material, so that flow separation is further weakened, and the efficiency and stability of a deformation fan for an aviation turbofan engine are improved under wide incoming flow Mach number and wide folding rotating speed;
the blades are divided into rotor blades and stator blades.
2. A textured fan for an aviation turbofan engine as defined in claim 1, wherein: under low folding rotation speed or low-speed cruising, the variable camber blades are driven to rotate around the shaft by a motor, and the mounting angles of the front blades, the rear blades and the front and rear blades of the variable camber stator are respectively increased, so that the air inlet attack angle of the rotor blade is reduced; further, aiming at the fan supercharging ratio adjusting requirement, the total supercharging ratio is improved by reducing the work load of the rotor tail blade along the anticlockwise rotation angle beta, and meanwhile, the static pressure ratio is improved by increasing the clockwise rotation angle gamma of the stator front blade and reducing the clockwise rotation angle delta of the stator tail blade; reducing the work load by increasing the rotation angle beta of the rotor tail vane along the anticlockwise direction, reducing the total supercharging ratio, and simultaneously reducing the static pressure ratio by reducing the rotation angle gamma of the stator front vane along the clockwise direction and increasing the rotation angle delta of the stator tail vane along the clockwise direction; on the other hand, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness and height chord length of the blade are regulated, smooth transition of the front blade, the tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is increased, the clearance between the blade tops is reduced, and the thrust of the engine under low-speed cruising is improved;
under high folding rotational speed or high-speed cruising, the motor drives the variable camber blades to rotate around the shaft, so that the installation angles of the front blades and the tail blades of the variable camber rotor and the front blades and the tail blades of the variable camber stator are respectively reduced, and the air inlet attack angle of the rotating stationary blade is reduced; further, aiming at the fan pressure ratio regulation requirement, the total pressure ratio is increased by increasing the work amount along the clockwise rotation angle beta of the rotor tail blade, and the static pressure ratio is increased by reducing the counter-clockwise rotation angle gamma of the stator front blade and increasing the counter-clockwise rotation angle delta of the stator tail blade; reducing the work load by reducing the rotor tail vane rotation angle beta clockwise, reducing the total supercharging ratio, and simultaneously reducing the static pressure ratio by increasing the stator front vane rotation angle gamma anticlockwise and reducing the stator tail vane rotation angle delta anticlockwise; on the other hand, the carbon fiber/piezoelectric material laminated structure on the blade surface is regulated and controlled by regulating the voltage to generate required deformation, so that the integral camber, thickness, height, chord length and the like of the blade are regulated, smooth transition of the front/tail blade and the middle blade is ensured, gap between the seam is reduced, and leakage loss is weakened; meanwhile, the shapes of the hub and the casing are regulated and controlled through voltage change, the flow area is regulated, and the clearance between the blade tops is reduced, so that the thrust of the engine under high-speed cruising is regulated.
3. A method for optimizing a textured fan for an aviation turbofan engine, for optimizing a textured fan for an aviation turbofan engine as defined in claim 1, characterized by: comprises the following steps of the method,
a) Determining the incoming flow speed of an engine according to the cruising speed of the aircraft, and rotating the front She Rao shaft and the tail She Rao shaft of the camber-changing rotor blade towards the increasing direction of the mounting angle when the incoming flow speed or the reduced rotating speed is lower than a design value; when the incoming flow speed or the folding rotational speed is higher than the design value, the front and the tail She Rao shafts of the camber-changing rotor blade rotate towards the direction of reducing the installation angle; determining the relative speed direction of the air inlet according to the axial incoming flow speed and the reduced rotating speed, combining a speed triangle, further determining the rotating angle of the front blade of the rotor by combining the attack angle loss characteristic, and simultaneously determining the rotating angle of the tail blade of the rotor by combining the total supercharging ratio requirement; determining the front blade rotation angle of the stator blade according to the attack angle loss characteristic of the stator blade and the absolute airflow angle of the rotor outlet, and determining the rotation angle of the stator tail blade according to the static pressure ratio and the outlet airflow direction;
b) According to the mechanical characteristics and piezoelectric driving deformation characteristics of the carbon fiber/piezoelectric material laminated structure, obtaining typical section blade profile and blade height aerodynamic force and centrifugal force deformation characteristics of the three-dimensional blade, and obtaining coupling deformation characteristics under the action of superposing certain voltage and position layout carbon fiber/piezoelectric material laminated structure;
c) Based on the step b), obtaining a three-section type deflection blade adopting a carbon fiber/piezoelectric material laminated structure, combining the stressed deformation characteristics under the two working conditions in the step a), obtaining the deformation characteristics of the blade shape, the front tail blade/middle blade gap under the coupling action of aerodynamic force, centrifugal force and piezoelectric drive, and obtaining the pneumatic loss and pressure ratio characteristics of the deformation fan through a numerical simulation tool; comparing the simulation result with an optimization target, and if the performance does not meet the requirement, adjusting the rotation angle of the front and rear blades of the rotor blade in the step a) and the layout of the piezoelectric material in the step b), and performing cyclic iteration until the pneumatic performance meets the index requirement, so as to realize the optimization of the deformed fan for the aviation turbofan engine.
4. A method of optimizing a morph fan for an aircraft turbofan engine as defined in claim 3, wherein: the layout optimization of piezoelectric materials realizes the high-precision micro-deformation of three layers of local, array and whole deformation fans, the realization method is that,
step (1): the piezoelectric material is integrally wrapped on the surface of the blade, so that the integral adjustment of the thickness, the bending degree, the angle, the curvature, the height and the chord length of the blade is carried out, and the integral adjustment with relatively large adjustment quantity and wide coverage range is realized;
step (2): the piezoelectric material is arranged at the part of the blade channel, so that the dihedral angle of the blade/channel, the local curvature of the blade, the gap between the front blade and the tail blade/the middle blade or the gap between the blade tops are controlled, and the precise adjustment with precise adjustment area and small coverage area is realized; the blade channel locally comprises a casing, an end wall or a suction surface corner region;
step (3): the piezoelectric material arrays are arranged in the blade channels, so that the device has the advantages of accurate adjustment area and large coverage area;
on the basis of realizing the adjustment of the steps (1), 2) and (3), the precise regulation and control of the vortex and shock waves of the blade channel are realized by fusing the advantages of large deformation amount of the variable camber blade driven by a mechanical structure and high deformation precision of the blade driven by an intelligent piezoelectric material, so that the flow separation is further weakened, and the efficiency and stability of the deformation fan for the aviation turbofan engine are improved under the conditions of wide incoming flow Mach number and wide folding rotational speed.
CN202310063107.XA 2023-01-17 2023-01-17 Deformed fan for aviation turbofan engine and optimization method Pending CN116398464A (en)

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CN202310063107.XA CN116398464A (en) 2023-01-17 2023-01-17 Deformed fan for aviation turbofan engine and optimization method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
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Publication Number Publication Date
CN116398464A true CN116398464A (en) 2023-07-07

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