CN116384010B - Engine bench fan rotor axial force evaluation method capable of being corrected in real time - Google Patents

Engine bench fan rotor axial force evaluation method capable of being corrected in real time Download PDF

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CN116384010B
CN116384010B CN202310638825.5A CN202310638825A CN116384010B CN 116384010 B CN116384010 B CN 116384010B CN 202310638825 A CN202310638825 A CN 202310638825A CN 116384010 B CN116384010 B CN 116384010B
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rotor
axial force
total
stage
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CN116384010A (en
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郭令
黄维娜
王丹丹
李波
杨韶
马健
张美芳
李晓明
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AECC Sichuan Gas Turbine Research Institute
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    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
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    • 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
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Abstract

The invention relates to the technical field of aeroengines, and discloses a real-time correction engine bench fan rotor axial force evaluation method, which fully utilizes the pneumatic characteristics of a fan component, solves the axial force of the fan rotor according to the geometric parameters of the fan component, the radial dimension of a sealing structure between rotors at all levels, the inlet static pressure and the outlet static pressure of the rotors at all levels, fully considers the situation that a fan possibly deviates from a designed working line in the calculation process, introduces a fan pressure ratio correction coefficient to correct the fan rotor axial force in real time, and can avoid the problems of poor adaptability and large calculation error of the existing fan rotor axial force calculation model caused by the fact that the working line is greatly influenced by the engine control rule.

Description

Engine bench fan rotor axial force evaluation method capable of being corrected in real time
Technical Field
The invention relates to the technical field of aeroengines, and discloses an engine rack fan rotor axial force evaluation method capable of being corrected in real time.
Background
In an aeroengine, the working line of a fan is greatly influenced by the throat area of a spray pipe and the control rule of high-low pressure slip, and the axial force of a fan rotor is a technical difficulty in calculating the axial force of a rotor of a complete machine rack.
The fan rotor axial force calculation involves parameters such as inlet and outlet airflow static pressure, density, axial speed (which cannot be directly tested by a rack) and flow of each stage of blades, so that the fan rotor axial force is a technical difficulty in fan rotor axial force calculation. The invention mainly solves the technical problem of calculating the axial force of the fan rotor. In the present invention, the axial force of the fan wheel rotor refers to the axial force of the fan rotor flow passage, and specifically comprises: blade body, blade tip and drum axial force.
In the aspect of the real-time calculation of the axial force of the rack fan rotor, a real-time calculation method of the axial force of the fan rotor of an aviation turbofan engine is provided by a patent CN 202210369069.6. The method still has the following defects:
a. the calculation model does not provide a fan rotor axial force calculation model according to the rotor axial force generation principle;
b. the fan rotor axial force calculation model has no universality, the calculation model under different working conditions needs to be solved, the workload is large, and meanwhile, the calculation model cannot be well adapted to the engine gas conversion stage (the working process that the total temperature and the total pressure of an engine inlet change continuously during a high altitude bench test), namely, the calculation model needs to be corrected in real time to adapt to the continuous change of the working conditions.
c. Because the fan working line is greatly influenced by the control rule of the whole machine (mainly influenced by the control rule of the spray pipe and the high-low pressure slip), when the actual working line of the fan deviates from the designed working line greatly, the relevant parameters of the calculation model change, if the real-time correction is not carried out, the calculation accuracy of the axial force of the fan rotor is influenced, namely, the calculation model needs to be corrected in real time to adapt to the change of the fan working line.
Patent 202211533183.4 (method, device, equipment and medium for evaluating axial force of compressor rotor) proposes a method for calculating axial force of compressor rotor in real time. However, compared with a compressor, the fan working line is greatly influenced by the control rule of the whole machine (mainly influenced by the control rule of the spray pipe and the high-low pressure slip), and when the fan working line deviates greatly from the design working line, a large error occurs when the patent calculation model is directly referenced to calculate the fan axial force.
Patent CN202211365989.7 (a rapid numerical calculation method for rotor axial force) proposes a method for calculating the rotor axial force of a blade part based on S2 data. The method still has the following defects: because the S2 data calculation is long in time consumption and is generally used for detailed analysis after the test, and cannot be calculated in real time in the test process, the method cannot be used for calculating the axial force of the fan rotor in real time.
Disclosure of Invention
The invention aims to provide a real-time correction engine rack fan rotor axial force evaluation method, which fully utilizes the pneumatic characteristics of design points of fan components, solves the axial force of the fan rotor according to the geometric parameters of the fan components, the radial dimension of sealing structures among all stages of rotors, corrected inlet static pressure and corrected outlet static pressure, fully considers the situation that a fan possibly deviates from a design working line in the calculation process, and introduces a fan pressure ratio correction coefficient to correct the axial force of the fan rotor in real time.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a real-time modifiable engine rack fan rotor axial force assessment method includes:
calculating inlet section Mach numbers and outlet section Mach numbers of each stage of rotor by adopting fluid simulation software according to the total fan inlet temperature, the total fan inlet pressure, the total fan outlet temperature, the total fan outlet pressure and the mass flow corresponding to different fan conversion rotating speeds under the design working condition air inlet conditions;
fitting a function model between the Mach number of the inlet section of each stage of rotor and the converted rotating speed and a function model between the Mach number of the outlet section of each stage of rotor and the converted rotating speed respectively;
substituting the actual conversion rotating speed of the fan in the working process of the engine into the corresponding function model, and calculating the actual Mach number of the inlet section and the actual Mach number of the outlet section of each stage of rotor of the fan;
according to the aerodynamic characteristic parameters of the fan component, the total inlet pressure and the total outlet pressure of the fan, solving the correction coefficient of the fan pressure ratio, the total inlet pressure of each stage of rotor and the total outlet pressure parameters of each stage of rotor; the aerodynamic characteristic parameters of the fan component comprise the total pressure ratio of the fan design points and the pressure ratio of the fan rotors at all levels;
solving the corrected inlet static pressure and the corrected outlet static pressure of each stage of rotor according to the actual Mach number of the inlet and outlet cross sections of each stage of rotor, the total inlet pressure of each stage of rotor and the total outlet pressure parameters of each stage of rotor;
solving an axial force static pressure component of the fan rotor according to blade roots and blade tip sizes of all levels of rotor blades of the fan component, radial sizes of sealing structures among all levels of rotors, inlet static pressures after all levels of rotor correction and outlet static pressures after all levels of rotor correction;
using the formulaCalculating an engine block fan rotor axial force evaluation value, wherein +.>For engine block fan rotor axial force evaluation value, < >>For the axial force static pressure component of the fan rotor, +.>The value range of the axial force static pressure component coefficient is 0.82-0.91.
And further, taking the fan conversion rotating speed under the design working condition air intake condition as an independent variable, taking the inlet section Mach number and the outlet section Mach number of each stage of rotor as dependent variables, and adopting an interpolation method and a polynomial fitting method to fit a corresponding function model.
Further, based on the aerodynamic parameters of the fan assembly, the total pressure of the fan inletAnd the total pressure of the fan outlet, solving the correction coefficient of the fan pressure ratioWherein->For the total number of stages of the fan rotor, pt is the total pressure of the fan inlet, +.>For the total pressure of the fan outlet->The point total pressure ratio is designed for the fan.
Further, the axial force static pressure component of the fan rotor,wherein->Is->Inlet area of stage fan rotor blade->Is->Stage fan rotor blade exit area,/-)>=1、2、3、......、/>，/>For the total number of stages of the fan rotor>Is->Tip area of the stage fan rotor blade; />Is->Inlet static pressure after stage rotor correction, +.>Is->And the outlet static pressure after the stage rotor is corrected.
Further, the static pressure component coefficient of the axial forceSpecific values according to->Calculated, wherein->Converted rotational speed for fan design point, +.>The rotational speed of the fan of the engine in the slow state is converted, < >>The conversion rotating speed is the actual working state of the fan.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, the aerodynamic characteristics (including the total pressure ratio of fan design points and the pressure ratio of each stage of rotor) of the fan component are fully utilized, the axial force of the fan rotor is solved according to the geometric parameters of the fan component, the radial dimension of a sealing structure between each stage of rotor, the inlet static pressure and the outlet static pressure of each stage of rotor, the situation that the fan possibly deviates from a design working line is fully considered in the calculation process, the fan pressure ratio correction coefficient is introduced to correct the axial force of the fan rotor in real time, and the problems that the existing fan rotor axial force calculation model is poor in adaptability and large in calculation error due to the fact that the working line is greatly influenced by the control rule of an engine can be avoided.
Drawings
Fig. 1 is a flowchart of a method for evaluating the axial force of a fan rotor of an engine rack, which can be corrected in real time in embodiment 1 or 2.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1, a method for evaluating axial force of a fan rotor of an engine rack capable of being corrected in real time includes:
calculating inlet section Mach numbers and outlet section Mach numbers of each stage of rotor by adopting fluid simulation software according to the total fan inlet temperature, the total fan inlet pressure, the total fan outlet temperature, the total fan outlet pressure and the mass flow corresponding to different fan conversion rotating speeds under the design working condition air inlet conditions;
fitting a function model between the Mach number of the inlet section of each stage of rotor and the converted rotating speed and a function model between the Mach number of the outlet section of each stage of rotor and the converted rotating speed respectively;
substituting the actual conversion rotating speed of the fan in the working process of the engine into the corresponding function model, and calculating the actual Mach number of the inlet section and the actual Mach number of the outlet section of each stage of rotor of the fan;
according to the aerodynamic characteristic parameters of the fan component, the total inlet pressure and the total outlet pressure of the fan, solving the correction coefficient of the fan pressure ratio, the total inlet pressure of each stage of rotor and the total outlet pressure parameters of each stage of rotor; the aerodynamic characteristic parameters of the fan component comprise the total pressure ratio of the fan design points and the pressure ratio of the fan rotors at all levels;
solving the corrected inlet static pressure and the corrected outlet static pressure of each stage of rotor according to the actual Mach number of the inlet and outlet cross sections of each stage of rotor, the total inlet pressure of each stage of rotor and the total outlet pressure parameters of each stage of rotor;
solving an axial force static pressure component of the fan rotor according to blade roots and blade tip sizes of all levels of rotor blades of the fan component, radial sizes of sealing structures among all levels of rotors, inlet static pressures after all levels of rotor correction and outlet static pressures after all levels of rotor correction;
using the formulaCalculating an engine block fan rotor axial force evaluation value, wherein +.>For engine block fan rotor axial force evaluation value, < >>For the axial force static pressure component of the fan rotor, +.>The value range of the axial force static pressure component coefficient is 0.82-0.91.
In the embodiment, the aerodynamic characteristics of the fan component are fully utilized, the axial force of the fan rotor is solved according to the geometric parameters of the fan component, the radial dimension of the sealing structure among the rotors at all levels, the inlet static pressure and the outlet static pressure of the rotors at all levels, the situation that the fan possibly deviates from a designed working line is fully considered in the calculation process, the fan pressure ratio correction coefficient is introduced to correct the axial force of the fan rotor in real time, and the problems that the existing fan rotor axial force calculation model is poor in adaptability and large in calculation error due to the fact that the working line is greatly influenced by the control rule of the engine can be avoided. The method provides technical support for monitoring the axial force of the fan rotor in real time in the scientific research test process and ensuring the safe operation of the whole machine, and also provides theoretical basis for the adjustment and optimization of the axial force of the rotor of the whole machine. The fan rotor axial force evaluation method can be widely applied to real-time monitoring of the axial force of the gantry fan in the scientific research test stage of the aeroengine, obtains the steady-state and dynamic characteristics of the axial force of the fan rotor meeting the engineering precision requirements, and can provide technical support for scientific research test safety and accelerating convergence of iterative design results of the axial force of the rotor.
Example 2
Referring to fig. 1, in this embodiment, a multistage fan rotor of an engine is taken as an example, and a method and an effect of evaluating an axial force of a fan rotor of a rack of an engine, which can be corrected in real time, according to the present invention are described in detail. The specific method comprises the following steps:
step one, calculating inlet section Mach numbers of each stage of rotor by adopting fluid simulation software according to total fan inlet temperature, total fan inlet pressure, total fan outlet temperature, total fan outlet pressure and mass flow corresponding to different fan conversion rotating speeds under the design working condition air inlet conditionAnd Mach number of the outlet section>。
Fitting a function model between the inlet section Mach number and the converted rotating speed of each stage of rotor and a function model between the outlet section Mach number and the converted rotating speed of each stage of rotor respectively according to the obtained inlet section Mach number and outlet section Mach number of each stage of rotor; in the embodiment, a fitting method is utilized, fan conversion rotating speeds under the corresponding design working condition air inlet conditions are used as independent variables, inlet section Mach numbers and outlet section Mach numbers of all stages of rotors are respectively used as dependent variables, and an interpolation method and a polynomial fitting method are adopted to solve the change relation of Mach numbers of inlet section airflows and outlet section airflows of all stages of rotors along with conversion rotating speeds:
wherein, the liquid crystal display device comprises a liquid crystal display device,、/>the rotation speed converted by the fan is obtained by data fitting>A functional expression that is an argument.
Substituting the actual conversion rotating speed of the fan in the working process of the engine into the corresponding function model, and calculating the actual Mach number of the inlet section and the actual Mach number of the outlet section of each stage of rotor of the fan;
step four, according to the aerodynamic characteristic parameters of the fan component, the total inlet pressure of the fan and the total outlet pressure of the fan, solving the correction coefficient of the fan pressure ratio, the total inlet pressure of each level of rotor and the total outlet pressure parameters of each level of rotor; the aerodynamic characteristic parameters of the fan component comprise the total pressure ratio of the fan design points and the pressure ratio of the fan rotors at all levels; fan pressure ratio correction factor in this embodimentWherein->For the total number of stages of the fan rotor, pt is the total pressure of the fan inlet, +.>For the total pressure of the fan outlet->The point total pressure ratio is designed for the fan.
The total pressure parameters of the inlet of each stage of rotor are according to the formulaCalculated get->Total pressure of rotor inlet of level 1 =>Equal to the total pressure Pt of the fan inlet;
the total pressure of the outlets of the rotors at all levels is according to the formulaCalculated, the final rotor outlet total pressure +.>Equal to the total pressure of the fan outlet->；
Wherein the method comprises the steps of=1、2、3、......、/>，/>For design point->Stage fan rotor pressure ratio,/-)>Is the total number of stages of the fan rotor.
Step five, solving corrected inlet static pressure and corrected outlet static pressure of each stage of rotor according to actual Mach number of inlet and outlet cross sections of each stage of rotor, total inlet pressure of each stage of rotor and total outlet pressure parameters of each stage of rotor;
in this embodiment, the inlet static pressure after correction of each stage of rotorAccording to the formulaCalculating to obtain; outlet static pressure after correction of each stage of rotor>According to the formulaCalculating to obtain;
wherein the method comprises the steps ofIs->Mach number of inlet section of stage rotor,/->Is->Mach number of the outlet section of the stage rotor,/->=1、2、3、......、/>，/>Is the total number of stages of the fan rotor,kis the specific heat ratio of air.
Step six, solving the axial force static pressure component of the fan rotor according to the blade root and blade tip size of each stage of rotor blade of the fan component, the radial size of a sealing structure between each stage of rotor, the inlet static pressure corrected by each stage of rotor and the outlet static pressure corrected by each stage of rotor; axial force static pressure component of fan rotor in this embodimentWherein->Is->Inlet area of stage fan rotor blade->Is->Stage fan rotor blade exit area,/-)>=1、2、3、......、/>，/>For the total number of stages of the fan rotor>Is->Stage fan rotor blade tip area.
Seventh, adopting a formulaCalculating an engine block fan rotor axial force evaluation value, wherein +.>For engine block fan rotor axial force evaluation value, < >>For the axial force static pressure component of the fan rotor, +.>The value range is 0.82-0.91 for the static pressure component coefficient of the axial force; in this embodiment the axial force static pressure component coefficient +.>According to the specific values of (2)Calculated, wherein->Converted rotational speed for fan design point, +.>The rotational speed of the fan of the engine in the slow state is converted, < >>The conversion rotating speed is the actual working state of the fan.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.

Claims (5)

1. A method for evaluating the axial force of a fan rotor of an engine rack capable of being corrected in real time, comprising the steps of:
calculating inlet section Mach numbers and outlet section Mach numbers of each stage of rotor by adopting fluid simulation software according to the total fan inlet temperature, the total fan inlet pressure, the total fan outlet temperature, the total fan outlet pressure and the mass flow corresponding to different fan conversion rotating speeds under the design working condition air inlet conditions;
fitting a function model between the Mach number of the inlet section of each stage of rotor and the converted rotating speed and a function model between the Mach number of the outlet section of each stage of rotor and the converted rotating speed respectively;
substituting the actual conversion rotating speed of the fan in the working process of the engine into the corresponding function model, and calculating the actual Mach number of the inlet section and the actual Mach number of the outlet section of each stage of rotor of the fan;
according to the aerodynamic characteristic parameters of the fan component, the total inlet pressure and the total outlet pressure of the fan, solving the correction coefficient of the fan pressure ratio, the total inlet pressure of each stage of rotor and the total outlet pressure parameters of each stage of rotor; the aerodynamic characteristic parameters of the fan component comprise the total pressure ratio of the fan design points and the pressure ratio of the fan rotors at all levels;
solving the corrected inlet static pressure and the corrected outlet static pressure of each stage of rotor according to the actual Mach number of the inlet and outlet cross sections of each stage of rotor, the total inlet pressure of each stage of rotor and the total outlet pressure parameters of each stage of rotor;
solving an axial force static pressure component of the fan rotor according to blade roots and blade tip sizes of all levels of rotor blades of the fan component, radial sizes of sealing structures among all levels of rotors, inlet static pressures after all levels of rotor correction and outlet static pressures after all levels of rotor correction;
using the formulaCalculating an engine block fan rotor axial force evaluation value, wherein +.>For engine block fan rotor axial force evaluation value, < >>For the axial force static pressure component of the fan rotor, +.>The value range of the axial force static pressure component coefficient is 0.82-0.91.
2. The method for evaluating axial force of engine-stand fan rotor according to claim 1, wherein the fan conversion rotation speed under the design condition of air intake is taken as an independent variable, the mach number of the inlet section and the mach number of the outlet section of each stage of rotor are taken as independent variables, and the fitting of the corresponding function model is performed by adopting an interpolation method and a polynomial fitting method.
3. The engine-stand fan rotor axial force evaluation method of claim 1 wherein the fan pressure ratio correction factor is solved based on the aerodynamic parameters of the fan components, the total fan inlet pressure and the total fan outlet pressureWherein->For the total number of stages of the fan rotor, pt is the total pressure of the fan inlet, +.>For the total pressure of the fan outlet->The point total pressure ratio is designed for the fan.
4. The engine-stand fan rotor axial force evaluation method of claim 1, wherein an axial force static pressure component of the fan rotor,wherein->Is->Inlet area of stage fan rotor blade->Is->Stage fan rotor blade exit area,/-)>=1、2、3、......、/>，/>For the total number of stages of the fan rotor>Is->Stage fan rotor bladeBlade tip area; />Is->The inlet static pressure after the stage rotor is corrected,is->And the outlet static pressure after the stage rotor is corrected.
5. The engine-stand fan rotor axial force evaluation method of claim 1, wherein the axial force static pressure component coefficientSpecific values according to->Calculated, wherein->Converted rotational speed for fan design point, +.>The rotational speed of the fan of the engine in the slow state is converted, < >>The conversion rotating speed is the actual working state of the fan.
CN202310638825.5A 2023-06-01 2023-06-01 Engine bench fan rotor axial force evaluation method capable of being corrected in real time Active CN116384010B (en)

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Publication number Priority date Publication date Assignee Title
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CN111914362A (en) * 2020-07-22 2020-11-10 中国航发沈阳发动机研究所 Self-adaptive method for turbofan engine model in research and development stage
CN114184390A (en) * 2022-02-16 2022-03-15 成都中科翼能科技有限公司 Gas turbine rotor axial force test sensor and parameter design method
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CN115544694A (en) * 2022-12-02 2022-12-30 中国航发四川燃气涡轮研究院 Method, device, equipment and medium for evaluating axial force of compressor rotor

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