CN115455767A - Blade arrival time accurate simulation method based on blade tip timing principle - Google Patents

Blade arrival time accurate simulation method based on blade tip timing principle Download PDF

Info

Publication number
CN115455767A
CN115455767A CN202211079809.9A CN202211079809A CN115455767A CN 115455767 A CN115455767 A CN 115455767A CN 202211079809 A CN202211079809 A CN 202211079809A CN 115455767 A CN115455767 A CN 115455767A
Authority
CN
China
Prior art keywords
blade
sensor
model
circumferential
axial
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.)
Pending
Application number
CN202211079809.9A
Other languages
Chinese (zh)
Inventor
张晓杰
胡殿印
王荣桥
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.)
Beihang University
Original Assignee
Beihang University
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 Beihang University filed Critical Beihang University
Priority to CN202211079809.9A priority Critical patent/CN115455767A/en
Publication of CN115455767A publication Critical patent/CN115455767A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • 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
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
    • G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
    • G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
    • G06T17/20—Finite element generation, e.g. wire-frame surface description, tesselation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/02—Reliability analysis or reliability optimisation; Failure analysis, e.g. worst case scenario performance, failure mode and effects analysis [FMEA]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/12—Timing analysis or timing optimisation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • 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

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Geometry (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Evolutionary Computation (AREA)
  • Computer Hardware Design (AREA)
  • General Engineering & Computer Science (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computational Mathematics (AREA)
  • Computer Graphics (AREA)
  • Software Systems (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention provides a blade arrival time accurate simulation method based on a blade tip timing principle, which comprises the following steps: (1) Establishing a blade tip timing sensor model based on the circumferential and axial layout information of the sensor; (2) Developing static and modal analysis based on a finite element analysis method, and establishing a rotating blade model; (3) Carrying out continuous processing on the blade tip finite element discrete nodes of the rotating blade model; (4) And establishing a blade arrival time model based on the sensor and the rotating blade model, judging the position relation between the sensor and the blade from the axial direction and the circumferential direction, and iteratively solving the blade arrival time. According to the method, the influence of axial position change on the simulation model in the motion process of the blade tip is considered through simulating the working process of the blade tip timing test system, and the result does not depend on the finite element grid density, so that more accurate blade arrival time can be obtained.

Description

Blade arrival time accurate simulation method based on blade tip timing principle
Technical Field
The invention belongs to the technical field of vibration testing of rotating blades of aerospace engines, and particularly relates to a blade arrival time accurate simulation method based on a blade tip timing principle.
Background
The high cycle fatigue failure of the rotor blade caused by vibration is a bottleneck problem which restricts the development and the service of the aeroengine in China. The vibration problem of advanced aircraft engines is more pronounced due to increased aerodynamic loads, reduced structural mechanical damping, and the use of lightweight structures. In order to ensure the safety and reliability of the engine, the blade needs to be subjected to vibration testing. Under the extreme service environment of high temperature, high pressure and high speed, the conventional strain electrometric method has low survival rate of a strain gauge and complex lead/slip ring transmission, and can only measure the strain of limited positions of limited blades. The blade tip timing testing technology is a most promising vibration testing means due to the advantages of non-contact, realization of vibration monitoring of full-period whole-stage blades and the like. However, the tip timing sampling signal is a time pulse signal and cannot be directly used for vibration analysis. In order to master the vibration characteristics of the blade, a corresponding vibration parameter identification algorithm needs to be developed.
When the vibration parameter identification algorithm is preliminarily evaluated, a numerical simulation model is usually adopted to obtain tip timing data, and the tip timing data mainly comprises a virtual signal model, a lumped parameter model and a finite element model. The virtual signal and the collective parameter model cannot reflect the geometric characteristics of the leaf/disk structure and the real dynamic characteristics of the leaf/disk structure, so that the vibration parameter identification algorithm has higher precision on a simulation model, but has larger error in practical application. The finite element model is used as a more complete numerical method and can reflect the detail characteristics and complex vibration modes of a blade/disk structure, but on one hand, the existing method only determines the arrival time of the blade through the circumferential position relation of the blade and the blade tip timing sensor, does not consider the axial position change of the blade and the sensor caused by deformation, and is not in accordance with the actual blade tip timing test process; on the other hand, the simulation result depends heavily on the finite element grid density, if the grid is sparse, the same node can only be captured in the blade motion process, and errors are brought to the simulation of the blade arrival time.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a blade tip timing principle-based accurate simulation method for blade arrival time, which is a blade arrival time simulation method independent of finite element grid density and considering axial position change in the blade motion process, constructs a blade tip timing simulation model capable of simulating the working process of a blade tip timing test system and reflecting the change of a sensor measuring point in the blade motion process, and serves and supports an aero-engine blade tip timing vibration test technology.
In order to achieve the purpose, the technical scheme adopted by the invention for solving the technical problems is as follows:
a blade arrival time accurate simulation method based on a blade tip timing principle is characterized in that a finite element method is utilized to simulate the working process of a blade tip timing test system, and a blade tip timing sensor model, a rotating blade model and a blade arrival time model are respectively constructed; carrying out polynomial curve fitting on the finite element discrete nodes of the blade tip to realize the grid density independence processing of the simulation model and the continuous processing of the rotating blade model; the method comprises the following steps of judging the relative position relation of a blade and a sensor from two dimensions of the axial direction and the circumferential direction, and realizing the accurate solution of the arrival time of the blade, wherein the method comprises the following steps:
step (1), establishing a blade tip timing sensor model based on the axial and circumferential layout information of the sensor;
step (2) developing static and modal analysis based on finite element method, establishing rotary blade model, and utilizing initial position u of blade ori Static deformation u sta And vibration displacement u vib Circumferential and axial coordinates of the rotating blade at different times from the representation of the rotation variation;
step (3) carrying out polynomial curve fitting on the circumferential and axial coordinates of the finite element nodes of the blade tip obtained in the step (2) at different moments to realize continuous processing of the rotating blade model;
and (4) determining the relative position relation between the sensor and the tip curve at different moments based on the tip timing sensor model and the continuously processed rotating blade model in the steps (1), (2) and (3), and establishing a blade arrival time model according to the relative position relation, wherein the moment meeting the measurement precision requirement of the sensor is the blade arrival time.
Further, in the step (1), the circumferential and axial coordinates of the nth sensor are respectively expressed as
Figure BDA0003833223930000021
Where ρ is the casing radius, θ n Is the circumferential angle of the sensor and,
Figure BDA0003833223930000026
for circumferential mounting errors, S n As axial coordinate of the sensor, Δ P nz Is an axial installation error.
Further, in the step (2), a rotating blade model is established by taking the node coordinate, the static deformation, the modal displacement scaling factor and the rotating speed of the finite element grid of the blade as input and considering the coordinate variation caused by rotation, static deformation and vibration, and the circumferential and axial coordinates of the blade at the time t are respectively expressed as
Figure BDA0003833223930000022
And U (z, t) = U ori (z)+u sta (z)+u vib (z, t) in which u ori As an initial position, u sta For static deformation, u vib For vibration displacement, ρ is the casing radius, Ω is the rotor rotation angular frequency, mod is the remainder symbol,
Figure BDA0003833223930000023
is the circumferential vibration displacement of the blade at time t, u vib And (z, t) is the axial vibration displacement of the blade at the time t.
Further, in the step (3), the finite element discrete nodes of the tip section in the rotating blade model are equivalent to curves, and polynomial curve fitting is performed on axial and circumferential coordinates of the nodes, which are expressed as
Figure BDA0003833223930000024
Wherein, the first and the second end of the pipe are connected with each other,
Figure BDA0003833223930000025
and U z Circumferential and axial coordinates, a, of the blade tip nodes, respectively 0 ～a n For polynomial fit parameters, n is the polynomial order.
Further, in the step (4), the upper and lower limits [ t ] of the blade arrival time measured by the nth sensor are determined by using the tip timing sensor model and the rotating blade model 1 ,t 2 ]And intermediate time t thereof 3 (ii) a Calculating t 3 At the moment, the relative position relation of the sensor and the blade tip fitting curve is corrected, and the upper and lower limits [ t ] of the arrival time of the blade are corrected according to the relative position relation 1 ,t 2 ](ii) a Iteratively updating the parameters of the sensor and the rotating blade model until the position difference between the sensor and the rotating blade model meets the measurement precision requirements of the sensor in the circumferential direction and the axial direction, namely
Figure BDA0003833223930000031
P nz -U z (t) | < Tol (z), wherein,
Figure BDA0003833223930000033
and P nz The circumferential and axial coordinates of the nth sensor,
Figure BDA0003833223930000034
and U z (t) circumferential and axial coordinates of the fitted curve of the lower lobe tip at time t,
Figure BDA0003833223930000032
and Tol (z) is the circumferential and axial measurement accuracy of the sensor.
Compared with the prior art, the invention has the advantages that:
(1) The invention can fully utilize the finite element analysis method of the blade/disc structure to improve the precision of the rotating blade simulation model;
(2) The rotating blade model established by the invention carries out continuous processing on the finite element discrete nodes of the blade tip, so that the simulation result does not depend on the grid density, the intersection point of the sensor and the blade tip section can be accurately captured, and the calculation precision of the blade arrival time is improved;
(3) The blade arrival time model established by the invention comprehensively considers the axial and circumferential position relation between the sensor and the blade tip section, and the blade arrival time is determined through the measurement accuracy in two directions, so that the blade arrival time model is more in accordance with the real situation.
Drawings
FIG. 1 is a general flow diagram of a tip timing simulation model;
FIG. 2 is a flow chart of a blade arrival time model.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The technical scheme of the accurate simulation method for the blade arrival time based on the blade tip timing principle is further explained below with reference to the attached drawings, and the related angles are all made of radians.
As shown in fig. 1, the method for accurately simulating the arrival time of a blade based on the tip timing principle of the present invention specifically includes the following steps:
the first step is as follows: and establishing a blade tip timing sensor model. Assuming that the blade tip timing test system comprises N sensors, taking the axial coordinate S, the circumferential angle theta, the casing radius rho and the installation error of the sensors as input, establishing circumferential and axial coordinate representation of a blade tip timing sensor model, namely:
Figure BDA0003833223930000041
P n (z)＝S n +ΔP nz ，n＝1,2,…,N (2)
in the formula (I), the compound is shown in the specification,
Figure BDA0003833223930000042
is the circumferential coordinate of the nth sensor, P n (z) is the axial coordinate of the nth sensor, Δ P nz For the axial mounting error of the nth sensor,
Figure BDA00038332239300000411
the circumferential installation error of the nth sensor is obtained.
The second step is that: and establishing a rotating blade model. The vane coordinate is changed from the initial position u ori U, static deformation sta And vibration displacement u vib And the rotation variation is determined. The method comprises the following specific steps:
(1) and carrying out finite element static force and modal analysis. Taking a finite element grid model of the blade, boundary conditions, material parameters and rotating speed as input, and performing static analysis under the action of centrifugal load and aerodynamic load by considering geometric nonlinearity, rotational softening and stress rigidization effects to obtain the static deformation u of the blade sta . And carrying out modal analysis containing prestress on the basis to obtain the natural vibration frequency and modal displacement of the blade.
(2) Aiming at a resonance state which is concerned in engineering, modal displacement is converted into vibration displacement u corresponding to different amplitudes by introducing a modal displacement scaling factor vib The expression is:
Figure BDA0003833223930000043
in the formula (I), the compound is shown in the specification,
Figure BDA0003833223930000044
is the vibration displacement of the blade in the circumferential direction and the axial direction at the time t, and mu is the modeThe scaling factor is shifted by a factor of two,
Figure BDA0003833223930000045
for circumferential and axial modal displacements, f is the natural vibration frequency of the blade.
(3) And establishing rotating blade models at different moments. The axial coordinates of the blade may be expressed as:
U(z,t)＝u ori (z)+u sta (z)+u vib (z,t) (4)
wherein U (z, t) is the axial coordinate of the blade at time t, U ori (z) and u sta (z) axial coordinate and axial static deformation, u, of finite element node of blade, respectively vib And (z, t) is the axial vibration displacement of the blade at the time t, and is determined by the step (2).
The circumferential coordinate of the blade may be expressed as:
Figure BDA0003833223930000046
in the formula (I), the compound is shown in the specification,
Figure BDA0003833223930000047
is the circumferential coordinate of the blade at time t,
Figure BDA0003833223930000048
and
Figure BDA0003833223930000049
respectively representing the circumferential coordinate and the circumferential static deformation of finite element nodes of the blade,
Figure BDA00038332239300000410
and (3) determining the circumferential vibration displacement of the blade at the time t by the step (2), wherein rho is the radius of the casing, omega is the rotation angular frequency of the rotor, and mod is a remainder symbol.
The third step: and carrying out continuous processing on the discrete nodes of the blade tip. The polynomial is utilized to fit finite element nodes of the blade tip in the forward rotation direction, the forward rotation direction of the gas compressor is the blade basin side, the turbine is the blade back side, and the fitting curve can be expressed as follows:
Figure BDA0003833223930000051
in the formula (I), the compound is shown in the specification,
Figure BDA0003833223930000052
and U z Respectively the circumferential and axial coordinates, a, of the blade tip node 0 ～a n For polynomial fit parameters, n is the polynomial order.
The fourth step: and establishing a blade arrival time model. The relative position relation between the sensor and the tip fitting curve at different moments is determined by using the tip timing sensor model and the continuously processed rotating blade model until the moment meeting the measurement precision requirement is found, namely the blade arrival time, and the calculation flow is shown in fig. 2. The method comprises the following specific steps:
(1) determining the upper and lower limits t of the blade arrival time corresponding to the nth sensor 1 ,t 2 ]And intermediate time t thereof 3 The expression is:
Figure BDA0003833223930000053
Figure BDA0003833223930000054
Figure BDA0003833223930000055
in the formula, delta theta is the circumferential angle of the sensor relative to the measured blade, omega is the rotation angular frequency of the rotor, rho is the radius of the casing,
Figure BDA0003833223930000056
and
Figure BDA0003833223930000057
the maximum static deformation and the maximum vibration displacement of the blade tip node are respectively.
(2) And judging the relative position relation between the sensor and the blade tip fitting curve. According to the third step, t is calculated 3 Time-lapse lower blade tip curve polynomial
Figure BDA0003833223930000058
On the basis, solving the circumferential coordinate of the point with the tip fitting curve being the same as the axial coordinate of the nth sensor
Figure BDA0003833223930000059
The expression is as follows:
Figure BDA00038332239300000510
in the formula, a 0 ～a n Is t 3 Polynomial fitting parameter of the temporal inferior lobe tip curve, P nz Is the axial coordinate of the nth sensor.
Then, the blade tip node is judged
Figure BDA00038332239300000511
And the nth sensor
Figure BDA00038332239300000512
The positional relationship therebetween. If it is
Figure BDA00038332239300000513
It means that the blade is leading the sensor and vice versa is lagging.
(3) And (5) iteratively solving the blade arrival time. Correcting the upper and lower limits of the arrival time of the blade according to the position relation in the step (2), and if the blade leads the sensor, comparing t with t 3 Giving an upper bound t to the arrival time in the next cycle 2 I.e. t 3 ＝t 2 . Otherwise, let t 3 ＝t 1 . Thus, a new upper and lower bound [ t ] for blade arrival time may be obtained 1 ,t 2 ]And intermediate time t thereof 3 。
Iteratively updating the blade tip timing sensor and the rotating blade model until the positions of the blade tip timing sensor and the rotating blade model meet the measurement accuracy requirement of the sensor, wherein the moment t at the moment is the arrival time of the blade, and the expression is as follows:
Figure BDA0003833223930000061
|P nz -U z (t)|＜Tol(z) (12)
in the formula (I), the compound is shown in the specification,
Figure BDA0003833223930000063
and P nz The circumferential and axial coordinates of the nth sensor,
Figure BDA0003833223930000064
and U z (t) are the circumferential and axial coordinates of the fitted curve of the lower lobe tip at time t,
Figure BDA0003833223930000062
and Tol (z) is the circumferential and axial measurement accuracy of the sensor.
The above embodiments are provided only for the purpose of describing the present invention, and are not intended to limit the scope of the present invention. The scope of the invention is defined by the appended claims. Various equivalent substitutions and modifications can be made without departing from the spirit and principles of the invention, and are intended to be within the scope of the invention.

Claims (5)

1. A blade tip timing principle-based blade arrival time accurate simulation method is characterized in that a finite element method is utilized to simulate the working process of a blade tip timing test system, and a blade tip timing sensor model, a rotating blade model and a blade arrival time model are respectively constructed; carrying out polynomial curve fitting on the finite element discrete nodes of the blade tip to realize the grid density independence processing of the simulation model; the method comprises the following steps of judging the relative position relation between a blade and a sensor from two dimensions of axial direction and circumferential direction, and realizing accurate solution of the arrival time of the blade, wherein the method specifically comprises the following steps:
step (1), establishing a blade tip timing sensor model based on the axial and circumferential layout information of the sensor;
step (2) developing static and modal analysis based on finite element method, establishing rotary blade model, and utilizing initial position u of blade ori Static deformation u sta And vibration displacement u vib Circumferential and axial coordinates of the rotating blade at different times from the representation of the rotation variation;
step (3) carrying out polynomial curve fitting on the circumferential and axial coordinates of the finite element nodes of the blade tip obtained in the step (2) at different moments to realize continuous processing of the rotating blade model;
and (4) determining the relative position relation between the sensor and the tip curve in the axial direction and the circumferential direction at different moments based on the tip timing sensor model and the continuously processed rotating blade model in the steps (1), (2) and (3), and establishing a blade arrival time model according to the relative position relation, wherein the moment meeting the measurement precision requirement of the sensor is the blade arrival time.
2. The method for accurately simulating the arrival time of the blade based on the tip timing principle of claim 1, wherein in the step (1), the circumferential coordinate of the nth sensor is expressed as
Figure FDA0003833223920000011
Axial coordinate is expressed as P n (z)＝S n +ΔP nz Where ρ is the casing radius, θ n For the angle of the circumference of the sensor,
Figure FDA0003833223920000012
for circumferential mounting errors, S n As axial coordinate of the sensor, Δ P nz Is an axial installation error.
3. The method for accurately simulating blade arrival time based on the blade tip timing principle as claimed in claim 2, wherein in the step (2), the node coordinates, the static deformation, the modal displacement and the modal shape of the finite element grid of the blade are usedThe displacement scaling factor and the rotating speed are used as input, a rotating blade model is established by considering coordinate variation caused by rotation, static deformation and vibration, and the circumferential coordinate of the blade at t moment is expressed as
Figure FDA0003833223920000013
Axial coordinate is expressed as U (z, t) = U ori (z)+u sta (z)+u vib (z, t) wherein u ori As an initial position, u sta For static deformation, u vib Rho is the radius of the casing, omega is the rotation angular frequency of the rotor, mod is a remainder symbol,
Figure FDA0003833223920000014
is the circumferential vibration displacement of the blade at t time, u vib And (z, t) is the axial vibration displacement of the blade at the time t.
4. The method as claimed in claim 3, wherein in the step (3), the finite element discrete nodes of the tip section of the rotating blade model are equivalent to curves, and polynomial curve fitting is performed on the axial and circumferential coordinates of the nodes, and the polynomial curve fitting is expressed as
Figure FDA0003833223920000021
Wherein the content of the first and second substances,
Figure FDA0003833223920000022
and U z Circumferential and axial coordinates, a, of the blade tip nodes, respectively 0 ～a n For polynomial fit parameters, n is the polynomial order.
5. The method for accurately simulating the arrival time of the blade based on the tip timing principle of claim 4, wherein in the step (4), the upper and lower limits [ t ] of the arrival time of the blade measured by the nth sensor are determined by using the tip timing sensor model and the rotary blade model 1 ,t 2 ]And intermediate time t thereof 3 (ii) a Calculating t 3 At time, the relative position relation between the sensor and the fitting curve of the blade tip is corrected according to the relative position relation, and the upper and lower limits t of the arrival time of the blade are corrected according to the relative position relation 1 ,t 2 ](ii) a Iteratively updating the parameters of the sensor and the rotating blade model until the position difference between the sensor and the rotating blade model meets the measurement precision requirements of the sensor in the circumferential direction and the axial direction, namely
Figure FDA0003833223920000023
|P nz -U z (t) | < Tol (z), wherein,
Figure FDA0003833223920000024
and P nz The circumferential and axial coordinates of the nth sensor,
Figure FDA0003833223920000025
and U z (t) are the circumferential and axial coordinates of the fitted curve of the lower lobe tip at time t,
Figure FDA0003833223920000026
and Tol (z) is the circumferential and axial measurement accuracy of the sensor.
CN202211079809.9A 2022-09-05 2022-09-05 Blade arrival time accurate simulation method based on blade tip timing principle Pending CN115455767A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202211079809.9A CN115455767A (en) 2022-09-05 2022-09-05 Blade arrival time accurate simulation method based on blade tip timing principle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211079809.9A CN115455767A (en) 2022-09-05 2022-09-05 Blade arrival time accurate simulation method based on blade tip timing principle

Publications (1)

Publication Number Publication Date
CN115455767A true CN115455767A (en) 2022-12-09

Family

ID=84302954

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211079809.9A Pending CN115455767A (en) 2022-09-05 2022-09-05 Blade arrival time accurate simulation method based on blade tip timing principle

Country Status (1)

Country Link
CN (1) CN115455767A (en)

Similar Documents

Publication Publication Date Title
US11860066B2 (en) Dynamic strain field measuring method and system for rotor blade based on blade tip timing
US12007309B2 (en) Non-contact dynamic strain field measuring method and system for rotating blade
CN109883380B (en) Rotor blade displacement field measuring method and system based on blade end timing
US8521493B2 (en) Rotating blade analysis
CN109790757B (en) Method and system for measuring rotor blade tip deflection using Blade Tip Timing (BTT)
CN102288362B (en) System and method for testing unsteady surface pressure of vibrating blade
CN110006563B (en) Distributed optical fiber decoupling measurement method for blade flapping and shimmy bending moment of helicopter
CN109883389B (en) Method and system for measuring dynamic strain field of rotating blade
CN110375690B (en) Rotating blade non-contact displacement field measurement method and system thereof
CN105352713A (en) Method used for realizing blade fatigue crack detection through static blade displacement detection
CN111507042A (en) Rotating blade dynamic stress measuring method and system based on blade end timing
Manwaring et al. Structures and Dynamics Committee Best Paper of 1996 Award: Inlet Distortion Generated Forced Response of a Low-Aspect-Ratio Transonic Fan
CN111507043A (en) Rotor blade dynamic stress field measuring method and system based on blade end timing
Ji-wang et al. Blade tip-timing technology with multiple reference phases for online monitoring of high-speed blades under variable-speed operation
Heath et al. A review of analysis techniques for blade tip-timing measurements
Zhang et al. Blade vibration stress determination method based on blade tip timing simulator and finite element method
CN113029481B (en) Method for measuring torsional vibration of blade
CN112763103B (en) Non-contact dynamic stress calibration method for rotor blade
Xu et al. Optimal placement of blade tip timing sensors considering multi-mode vibration using evolutionary algorithms
CN117131608A (en) Excitation disk method based on optimal annular quantity distribution
CN115455767A (en) Blade arrival time accurate simulation method based on blade tip timing principle
CN113051661A (en) High-temperature airflow dynamic total pressure intelligent soft measurement method based on micro cavity multi-dynamics
Hartung et al. A Practical Approach for Evaluation of Equivalent Linear Damping From Measurements of Mistuned and/or Non-Linear Stages and Forced Response Validation
CN110118108B (en) Method for measuring distortion degree of blade profile of engine rotor blade in rotating state
CN115435894A (en) Blade tip timing vibration stress inversion method based on simulated annealing algorithm

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