CN110362961B - Method for determining bird strike test parameters of fan rotor blade of aircraft engine - Google Patents

Method for determining bird strike test parameters of fan rotor blade of aircraft engine Download PDF

Info

Publication number
CN110362961B
CN110362961B CN201910735493.6A CN201910735493A CN110362961B CN 110362961 B CN110362961 B CN 110362961B CN 201910735493 A CN201910735493 A CN 201910735493A CN 110362961 B CN110362961 B CN 110362961B
Authority
CN
China
Prior art keywords
blade
bird
speed
determining
engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201910735493.6A
Other languages
Chinese (zh)
Other versions
CN110362961A (en
Inventor
张海洋
王相平
杜少辉
曹航
陈育志
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Engine Research Institute
Original Assignee
AECC Shenyang Engine Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN201910735493.6A priority Critical patent/CN110362961B/en
Publication of CN110362961A publication Critical patent/CN110362961A/en
Application granted granted Critical
Publication of CN110362961B publication Critical patent/CN110362961B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • 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
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Abstract

The application belongs to the technical field of bird strike tests of aero-engines, and particularly relates to a method for determining bird strike test parameters of fan rotor blades of an aero-engine. The method comprises the steps of firstly establishing a blade cascade cutting model of a fan rotor blade bird strike test, determining a damage mode of the blade, then determining a speed component VC perpendicular to the tangential direction of a leading edge blade profile, and finally determining the maximum value of the speed component VC in different damage modes at each flight stage and corresponding fan rotor blade bird strike test parameters under the maximum value.

Description

Method for determining bird strike test parameters of fan rotor blade of aircraft engine
Technical Field
The application belongs to the technical field of bird strike tests of aero-engines, and particularly relates to a method for determining bird strike test parameters of fan rotor blades of an aero-engine.
Background
The bird strike of the aircraft engine is always a major accident seriously damaging the flight safety of an aircraft, after the bird strike of the aircraft engine, the bird can firstly strike a fan rotor blade at the inlet of the engine, so that the blade is sunken, deformed, torn, cracked, dropped and even broken, a series of secondary damages are caused, the pneumatic performance of the blade is reduced, the thrust of the engine is reduced, the engine is damaged, the engine is flameout, the broken blade even breaks through a casing and flies out, the safety of passengers is directly damaged, the machine is damaged, and the death and death of people occur, so that huge economic loss is generated. With the improvement of the engine development technology, advanced engine fan rotor blades develop towards a high-efficiency thin-thickness integral blade disc, the bird impact resistance of the blades is weakened, the maintenance cost caused by bird impact is increased, meanwhile, the development of military and civil aviation industry and the increase of environmental protection force lead to the fact that the number of airplane flight times, the number of hours and the number of birds are more and more, the probability and the number of bird impact of an aircraft engine are greatly increased, and in order to ensure the flight safety and economy, the bird impact resistance design and evaluation of the fan rotor blades in the engine design stage become an extremely important content in modern engine design.
In the design and evaluation of bird impact resistance of an aircraft engine, one of the most basic works is to determine the design evaluation state and parameters, and the current determination method is completely based on the requirements of the terms of GJB241A-2010 and CCAR-33R2, for example, according to the 3.8.6.1 requirements in GJB241A-2010, the evaluation state and parameters include: the bird speed is equal to the takeoff speed of the airplane, and the rotating speed of the engine is the maximum state rotating speed; the bird speed is equal to the cruising speed of takeoff within the height of 3000m, and the rotating speed of the engine is the cruising specified speed; the bird speed is equal to the gliding speed of the airplane in the height of 1500m, and the rotating speed of the engine is the specified gliding rotating speed; the bird speed is equal to the maximum limit flying speed of the airplane within 2500m of height, and the engine rotating speed is the maximum state rotating speed or the maximum continuous state rotating speed, and the maximum damage is the main speed of the bird. The collision positions of the small birds are irregularly distributed on the inlet area, and the medium and large birds deal with key positions on the front side of the engine.
In the prior art, the working environment and the working state of a specific aircraft engine and the structural characteristics of fan rotor blades are not considered, and particularly for an advanced engine, compared with the prior engine, the use characteristics and the fan blade structure are greatly changed, and the method for determining the evaluation state and parameters completely according to the standard requirements cannot completely meet the actual engine condition. In addition, when the parameters are actually determined, the parameters which are qualitatively specified are a large range of values, for example, the takeoff speed can be 50 m/s-150 m/s, so that a method capable of determining the parameters under the most severe conditions in a certain range is needed, and the impact positions are qualitatively specified and further must be determined in the actual determination process. 4 evaluation states are specified in the airworthiness requirement, the evaluation states are more, and the evaluation and verification period and the economic cost are larger.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a method for determining bird strike test parameters of a fan rotor blade of an aircraft engine, comprising:
establishing a blade cascade cutting model of a fan rotor blade bird strike test, and determining the relative speed VS of a bird relative to an engine blade, the included angle alpha of the relative speed VS and the engine axis, and the relation between the leading edge blade profile angle theta of a blade cascade and the relation among the blade cascade, wherein the relative speed VS is determined by the tangential speed V2 of the bird striking at the striking position radius R of the blade according to the relative speed V1 of the bird relative to the engine axis;
determining a damage mode of the blade according to the included angle alpha and the leading edge blade profile angle theta, wherein the damage mode comprises a blade basin side impact damage mode when the included angle alpha is larger than the leading edge blade profile angle theta and a blade back side impact damage mode when the included angle alpha is smaller than the leading edge blade profile angle theta;
determining a velocity component VC of the relative velocity VS perpendicular to the tangential direction of the leading edge blade profile according to the blade cascade cutting model;
determining the engine rotating speed and the flying speed in each flying stage specified by airworthiness regulations, and determining the maximum value of the speed component VC in the blade basin side impact damage mode and the blade back side impact damage mode in each flying stage; and
and determining the engine speed, the impact position radius R and the bird speed under the blade basin side impact damage mode and the engine speed, the impact position radius R and the bird speed under the blade back side impact damage mode according to the maximum value of the speed component VC.
Preferably, the determining the relative speed VS of the bird with respect to the engine blade and the included angle α between the relative speed VS and the engine axis includes:
determining the relative speed V1 of the bird with respect to the engine axis;
determining the tangential velocity V2 of the bird impacting on the blade at the impact position radius R;
synthesizing the relative velocity VS from the relative velocity V1 and the tangential velocity V2; and
and determining an included angle alpha according to the relative speed V1 and the relative speed VS.
Preferably, determining the leading edge profile angle θ of the cascade comprises:
obtaining a change curve of a blade profile angle of the front edge of a fan rotor blade along with the radius of a blade body; and
and determining a leading edge profile angle theta according to the blade body radius determined during the structural design of the engine fan rotor blade.
Preferably, the velocity component VC is:
Figure GDA0003847897490000031
wherein W is the engine speed.
Preferably, the flight phases comprise a takeoff climb phase, a cruise phase, an air maximum speed state phase, a glide-down phase and a landing phase.
Preferably, the lower limit value of the speed of the flying bird is 50m/s.
According to the method and the device, an influence rule curve of bird impact parameters can be obtained, so that specific parameters corresponding to each evaluation state are determined, the considered parameter range is more comprehensive and reasonable, the bird impact mode and the corresponding damage type can be estimated, the evaluation states can be simplified according to two bird impact modes with serious damage, the evaluation states and the verification states are reduced, and the cycle cost and the economic cost are greatly saved.
Drawings
FIG. 1 is a flow chart of an embodiment of a method for determining bird strike test parameters for an aircraft engine fan rotor blade according to the present application.
FIG. 2 is a schematic view of a cascade cutting model of the present application.
FIG. 3 is a schematic diagram of an impact energy prediction model of the present application.
FIG. 4 is a schematic illustration of the variation of β with bird speed and impact radius for a takeoff climb flight condition of the present application at 4500rmp rpm.
Fig. 5 is a graph illustrating the vertical velocity VC under a certain flight condition according to the bird speed and the impact radius.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
As shown in fig. 1, the present application provides a method for determining bird strike test parameters of a fan rotor blade of an aircraft engine, comprising:
s1, establishing a blade cascade cutting model of a fan rotor blade bird impact test, and determining the relative speed VS of the flying bird relative to the engine blade, the included angle alpha between the relative speed VS and the engine axis, and the relation between the leading edge blade profile angle theta of the blade cascade and the relation among the blade cascade, wherein the relative speed VS is determined by the tangential speed V2 of the flying bird impacting on the radius R of the impact position of the blade relative to the relative speed V1 of the flying bird relative to the engine axis.
In the present application, the blade bird strike parameters include bird speed, engine speed, and strike location radius.
A bird strike fan blade cascade cutting model was created as shown in figure 2. The cylinder in the figure represents the bird body, flying towards the blades at a speed V1, in the direction along the engine axis, i.e. in the direction of the intake of the engine in the figure; the bird strikes to the position (the striking position radius R) with the radius R of the blade, the blade cascade is a schematic view of the radius R section of the fan blade, and theta is the leading edge blade profile angle of the radius R section; the blades rotate according to the physical rotating speed W of the fan, and the tangential speed of the impact position is V2.
A local coordinate system is established on the cascade where, in addition to the velocity V1 of the bird flying towards the blades, there is a velocity, opposite to the direction of rotation of the engine, of magnitude V2. V1 and V2 combine to be VS, the speed of the bird relative to the impinging blade, and the resultant speed VS makes an angle α with the axis of the engine, i.e., the angle of the bird relative to the impinging blade.
The relationship between the parameters is as follows:
V2＝W×R
Figure GDA0003847897490000041
Figure GDA0003847897490000042
and S2, determining a damage mode of the blade according to the included angle alpha and the leading edge blade profile angle theta, wherein the damage mode comprises a blade basin side impact damage mode when the included angle alpha is larger than the leading edge blade profile angle theta and a blade back side impact damage mode when the included angle alpha is smaller than the leading edge blade profile angle theta.
Wherein the leading edge profile angle θ may be determined at the stage of engine fan rotor blade structural design:
obtaining a change curve of a blade profile angle of a front edge of a fan rotor blade along with the radius of a blade body; and determining a leading edge profile angle theta according to the blade body radius determined during the structural design of the engine fan rotor blade.
In this step, referring to fig. 2 and 3, β is defined as an included angle between the angle α of the relative impact blade and the blade profile angle θ of the leading edge of the blade, that is, β = α - θ, and according to the positive-negative relationship of β, the manner in which the bird impacts the blade can be determined, and the damage mode of the blade can be estimated.
(1) Beta is positive, i.e. the angle alpha of the blade relative to impact is greater than the profile angle theta of the leading edge of the blade
Observing from local coordinate system on the cascade, the bird directly strikes blade basin side, in actual process, because the bird body is longer, the bird body can be cut by the blade leading edge, and the fritter bird body that cuts can be collided with blade basin side, takes place to warp, and remaining bird body continues the flight, strikes follow-up blade, and this striking mode definition is basin side striking, and the blade can appear by striking position to the dorsal side subside after being strikeed, and whole blade is crooked to the dorsal side.
(2) When beta is negative, i.e. the angle alpha of the blade relative to the impact is smaller than the profile angle theta of the leading edge of the blade
The local coordinate system observation on the cascade of follow-up, the bird directly strikes the blade dorsal part, and in the actual process, because the bird body is longer, the bird body can be cut by the blade leading edge, cuts remaining bold bird body and can collide with the blade dorsal part, takes place to warp, and remaining fritter bird body continues the flight, strikes follow-up blade, and this striking mode definition is the dorsal part striking, and the blade can appear by striking position to basin side sunken after being strikeed, and whole blade is crooked to the basin side.
(3) When beta is close to 0, i.e. the angle alpha of the relative impact blade is equal to the profile angle theta of the leading edge of the blade
When viewed from a local coordinate system on the blade cascade, the bird directly impacts the front edge of the blade and flies backwards by being divided into two halves by the cutting of the front edge, and the impact mode is defined as the cutting of the front edge, and the damage to the blade is small in the mode.
In summary, the bird strike pattern can be interpreted from the positive and negative values of β, and the damage pattern of the blade after being struck can be estimated. According to the parameter correlation, beta is obtained by calculating a relative impact blade angle alpha and a blade leading edge blade profile angle theta, the alpha angle is obtained by calculating a bird speed V1, an engine rotating speed W and an impact position radius R, the blade leading edge blade profile angle theta is determined by blade structure design, and a specific numerical value is determined according to the impact radius R, so that beta can be obtained by calculating according to the impact parameters of the bird speed V1, the engine rotating speed W, the impact position radius R and the engine structure parameter theta, and the influence rule of bird impact parameters on an impact mode and a blade damage mode is analyzed.
And S3, determining a speed component VC of the relative speed VS, which is perpendicular to the tangential direction of the leading edge blade profile, according to the blade cascade cutting model.
Step S3 is actually to establish an impact energy estimation model based on the bird-impacting fan blade cascade cutting model, as shown in fig. 3, where VS is the speed of the bird relative to the impacting blade, α is the angle of the bird relative to the impacting blade, θ is the blade leading edge profile angle, and β is the included angle between the relative impacting blade angle α and the blade leading edge profile angle θ, and these parameters are consistent with the parameter definition mode in the bird-impacting fan blade cascade cutting model. The kinetic energy represented by the bird's velocity VS against the impacting blade can be decomposed into two directions of kinetic energy, one with little change during the impact process along the tangent to the leading edge profile, and the other perpendicular to the tangent to the leading edge profile, i.e., VC in fig. 3 (the perpendicular component of VS, also called the vertical velocity), which eventually becomes 0, and this kinetic energy of velocity is transferred to the blade by the impact, causing damage to the blade, and thus VC can affect the degree of damage to the blade. The formula for VC is as follows:
Figure GDA0003847897490000061
in conclusion, the damage degree of the bird striking blade is compared according to the size of VC, and VC can be obtained by calculating bird speed V1, engine rotating speed W, striking position radius R and blade leading edge blade profile angle theta, so that the influence rule of the damage degree under different striking modes and blade damage modes can be analyzed according to bird striking parameters and fan blade structure parameters.
And S4, determining the engine rotating speed and the flying speed in each flying stage specified by airworthiness regulations, and determining the maximum value of the speed component VC in the blade basin side impact damage mode and the blade back side impact damage mode in each flying stage.
In the step, the typical flight tasks of the airplane assembled with the engine are classified and unified, the typical flight state of the airplane and the physical rotating speed range of the engine are obtained according to the working state parameters of the engine, as shown in the table 1,
TABLE 1 typical flight status of an aircraft and range of engine physical speeds
Figure GDA0003847897490000062
In the step, a blade bird strike parameter influence analysis technology is adopted to obtain an influence change curve of bird strike parameters such as bird strike speed, engine rotating speed and strike radius of the airplane in a typical state on a blade bird strike mode and a damage degree, and obtain a strike mode in the typical analysis state and bird strike parameters (bird speed, engine physical rotating speed and strike position) under the condition of maximum damage in each mode
Taking the takeoff climb phase 4500rmp as an example, the variation curves of the bird speed, the beta (positive and negative determining the impact mode and the damage mode) and the VC (determining the damage degree) under the impact radius in different states are obtained and are shown in fig. 4 and fig. 5.
And S5, determining the engine speed, the radius R of the impact position and the bird speed under the blade basin side impact damage mode and the engine speed, the radius R of the impact position and the bird speed under the blade back side impact damage mode according to the maximum value of the speed component VC.
Step S5 is based on step S4, first, in each flight state, each parameter in the blade basin side impact damage mode and the blade back side impact damage mode is determined, and as can be seen from the curve of fig. 5, the lower the bird speed (50 m/S), the greater the vertical velocity VC is, and the radius R of the impact position can be determined from the curve in the case of the same bird speed. From this curve, the bird strike pattern and the specific parameters of the pattern with maximum damage within the parameter range under different typical flight conditions are obtained, as shown in table 2.
TABLE 2 bird strike patterns and maximum damage parameter combinations for each typical flight phase
Figure GDA0003847897490000071
Figure GDA0003847897490000081
And then, the step S5 is also used for respectively selecting the maximum vertical impact speed VC under the impact of the basin side and the back side according to the table 2, dividing the impact modes into two impact modes according to the analysis result, wherein the maximum damage impact positions of the two impact modes are the same, and simplifying the evaluated typical states into 2 types according to the impact modes and the damage severity degree of the two impact modes, wherein the simplified states are shown in the table 3 and are respectively the working conditions with the maximum vertical impact speed under the two impact modes, namely the maximum damage condition.
TABLE 3 Final estimated flight status and specific parameters after simplification
Figure GDA0003847897490000082
According to the requirements of the GJB241A-2010, the evaluation states must include four states of take-off, cruise, maximum and landing, the method considers 5 states of take-off climb, cruise, maximum in air, glide and landing, and the considered flight altitude is larger than the requirement of the GJB241A-2010, so that the method can completely meet the requirement of the GJB241A-2010 on the flight state and is considered more comprehensively. According to the bird collision evaluation state and the bird collision evaluation parameter determination method, the adaptability to an actual engine is ensured according to the flight task of an airplane assembled by the actual engine, the working state of the engine and the structural characteristics of the fan rotor blade, and meanwhile, the requirements of GJB241A-2010 and airworthiness regulations can be met. The evaluation state and parameters determined by the technology of the invention can not only ensure the adaptability to the actual engine, but also ensure the conformity to the standard specification.
By adopting the technology of the invention, the influence rule curve of bird collision parameters can be obtained, so that the specific parameters corresponding to each evaluation state are determined, and the considered parameter range is more comprehensive and reasonable.
The method can predict the bird impact modes and the corresponding damage types, simplify the evaluation state according to two bird impact modes with serious damage, reduce the evaluation state and the verification state under the condition of obtaining military approval, and greatly save the cycle cost and the economic cost.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (4)

1. The method for determining bird strike test parameters of the fan rotor blade of the aircraft engine is characterized by comprising the following steps:
establishing a cascade cutting model of a fan rotor blade bird strike test, and determining the relative speed VS of a bird relative to an engine blade, the included angle alpha of the relative speed VS to the engine axis, the leading edge profile angle theta of a cascade and the relation among the cascade, wherein the relative speed VS is determined by the tangential speed V2 of the bird striking at the striking position radius R of the blade according to the relative speed V1 of the bird relative to the engine axis, and wherein the determining of the relative speed VS of the bird relative to the engine blade and the included angle alpha of the relative speed VS to the engine axis comprises the following steps: determining the relative speed V1 of the bird with respect to the engine axis; determining the tangential velocity V2 of the bird impacting on the radius R of the impact position of the blade; synthesizing the relative velocity VS from the relative velocity V1 and the tangential velocity V2; determining an included angle alpha according to the relative speed V1 and the relative speed VS;
determining a damage mode of the blade according to the included angle alpha and the leading edge blade profile angle theta, wherein the damage mode comprises a blade basin side impact damage mode when the included angle alpha is larger than the leading edge blade profile angle theta and a blade back side impact damage mode when the included angle alpha is smaller than the leading edge blade profile angle theta;
determining a velocity component VC of the relative velocity VS perpendicular to the tangential direction of the leading edge blade profile according to the blade cascade cutting model, wherein the velocity component VC is as follows:
Figure FDA0003847897480000011
wherein W is the engine speed, and beta is the included angle between the included angle alpha and the leading edge profile angle theta;
determining the engine speed and the bird speed at each flight stage specified by airworthiness regulations, obtaining the change curves of bird speeds, included angles beta under impact radiuses and speed components VC at different states, analyzing the influence rules of damage degrees under different impact modes and blade damage modes according to bird impact parameters and fan blade structure parameters, and determining the maximum value of the speed components VC when a blade basin side impact damage mode and a blade back side impact damage mode at each flight stage; and
and determining the engine speed, the radius R of the impact position and the bird speed under the blade basin side impact damage mode and the engine speed, the radius R of the impact position and the bird speed under the blade back side impact damage mode according to the maximum value of the speed component VC.
2. The aircraft engine fan rotor blade bird strike test parameter determination method of claim 1, wherein determining the leading edge profile angle θ of the cascade comprises:
obtaining a change curve of a blade profile angle of the front edge of a fan rotor blade along with the radius of a blade body; and
and determining a leading edge profile angle theta according to the blade body radius determined during the structural design of the engine fan rotor blade.
3. The method of determining aircraft engine fan rotor blade bird strike test parameters of claim 1, wherein the flight phase comprises a takeoff climb phase, a cruise phase, an air maximum speed state phase, a glide phase, and a landing phase.
4. The method of determining aircraft engine fan rotor blade bird strike test parameters of claim 1, wherein the bird speed lower limit is 50m/s.
CN201910735493.6A 2019-08-09 2019-08-09 Method for determining bird strike test parameters of fan rotor blade of aircraft engine Active CN110362961B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910735493.6A CN110362961B (en) 2019-08-09 2019-08-09 Method for determining bird strike test parameters of fan rotor blade of aircraft engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910735493.6A CN110362961B (en) 2019-08-09 2019-08-09 Method for determining bird strike test parameters of fan rotor blade of aircraft engine

Publications (2)

Publication Number Publication Date
CN110362961A CN110362961A (en) 2019-10-22
CN110362961B true CN110362961B (en) 2022-11-22

Family

ID=68223576

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910735493.6A Active CN110362961B (en) 2019-08-09 2019-08-09 Method for determining bird strike test parameters of fan rotor blade of aircraft engine

Country Status (1)

Country Link
CN (1) CN110362961B (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110889172B (en) * 2019-12-04 2023-03-28 中国直升机设计研究所 Method for prefabricating impact damage of helicopter rotor system
CN113495002B (en) * 2020-04-03 2023-01-06 中国航发商用航空发动机有限责任公司 Rotary impact test device for non-full-ring fan blade of aero-engine
CN111625973B (en) * 2020-04-15 2022-06-10 中国电子产品可靠性与环境试验研究所（（工业和信息化部电子第五研究所）（中国赛宝实验室）） Bird collision aircraft wing analysis method and device, computer equipment and storage medium
CN111579190B (en) * 2020-04-27 2021-05-25 南京航空航天大学 Horizontal ejection-impact type blade bird-cutting test device and test method
CN111737892B (en) * 2020-05-20 2024-03-29 南京航空航天大学 Equivalent safety-based ice impact engine fan rotor coincidence analysis method
CN114580094B (en) * 2022-01-19 2023-07-28 南京航空航天大学 Bird strike injury engineering prediction method for rotating state of metal blade
CN115114735B (en) * 2022-07-26 2024-03-19 中国航发沈阳发动机研究所 Bird strike resistant design method for aeroengine fan rotor blade shoulder

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2000095195A (en) * 1998-07-24 2000-04-04 Kazuo Ariyoshi Device to prevent bird strike for airplane
JP6232815B2 (en) * 2013-08-05 2017-11-22 株式会社Ihi Projectile for simulating bird strike
DE102015120660A1 (en) * 2015-11-27 2017-06-01 Airbus Defence and Space GmbH Aircraft inspection system
CN105421244B (en) * 2015-12-10 2017-07-28 江苏法尔胜缆索有限公司 A kind of preparation method of main rope of suspension bridge Prefabricated parallel preshaping of wire strand
CN105760623A (en) * 2016-03-16 2016-07-13 中国直升机设计研究所 Method for determining allowable defects of helicopter composite main rotor blade
CN106251068B (en) * 2016-08-01 2019-08-16 中国航空工业集团公司沈阳发动机设计研究所 A kind of total state bird based on fan part bird impact tests result hits appraisal procedure
CN106649937B (en) * 2016-09-27 2020-04-21 南京航空航天大学 Aero-engine fan bird-sucking airworthiness analysis method

Also Published As

Publication number Publication date
CN110362961A (en) 2019-10-22

Similar Documents

Publication Publication Date Title
CN110362961B (en) Method for determining bird strike test parameters of fan rotor blade of aircraft engine
CN105574247B (en) A kind of aero-engine benchmark test loading spectrum preparation method
Van Zante Progress in open rotor research: A US perspective
Liu et al. UAV airborne collision to manned aircraft engine: Damage of fan blades and resultant thrust loss
CN110030110B (en) Method and device for improving aerodynamic stability of shipboard aircraft engine based on state recognition
Puneeth et al. Influence of bird mass and impact height on the fan-blade of an aero-engine
CN111046490A (en) Grid size inversion method in foreign object damage gap analysis
CN112417595B (en) Method for evaluating installation thrust of aircraft engine
CN115114735A (en) Bird-strike-resistant design method for aeroengine fan rotor blade shoulder
CN111737892B (en) Equivalent safety-based ice impact engine fan rotor coincidence analysis method
Xie et al. Numerical investigation of inlet distortion for different rear mounted engine installations at taking-off conditions
Wirkowski Modelling the characteristics of axial compressor of variable flow passage geometry, working in the gas turbine engine system
CN107743552B (en) Method for manufacturing a turbomachine fan
Kritikos et al. Prediction of certification noise levels generated by contra-rotating open rotor engines
CN110987388B (en) Method for equivalent machining notch based on notch fatigue strength
Leverton Twenty-five years of rotorcraft aeroacoustics: Historical prospective and important issues
CN112733398A (en) Method for determining repair-free limit of impact damage of pit-type hard object
CN115114736B (en) Bird strike resistant design method for front edge of fan rotor blade of aero-engine
Chamberlin The Altitude Wind Tunnel (AWT)-A unique facility for propulsion system and adverse weather testing
Frankenberger Large engine uncontained debris analysis
Mathy The aeronautic research programme of the German Federal Ministry of Economics and Technology (BMWi)
CN115238504A (en) Method for determining key parameters of bird swallowing of aircraft engine based on local damage of blade
CN115600344A (en) Rapid prediction method for flutter of compression system of aircraft engine
Borst Aerodynamic Design and Analysis of Propellers for Mini-remotely Piloted Air Vehicles: Ducted propellers
CN115266119A (en) Determination method for foreign object damage assessment test run program of aero-engine

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant