CN116205007A - Real-time evaluation method and device for axial force of high-pressure turbine rotor - Google Patents

Real-time evaluation method and device for axial force of high-pressure turbine rotor Download PDF

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CN116205007A
CN116205007A CN202310466068.8A CN202310466068A CN116205007A CN 116205007 A CN116205007 A CN 116205007A CN 202310466068 A CN202310466068 A CN 202310466068A CN 116205007 A CN116205007 A CN 116205007A
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pressure turbine
axial force
outlet
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CN116205007B (en
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郭令
马波
黄维娜
赵江伟
李波
马健
李晓明
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AECC Sichuan Gas Turbine Research Institute
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Abstract

The invention relates to the technical field of aero-engines, and discloses a real-time evaluation method and device for axial force of a high-pressure turbine rotor, wherein a rotor axial force evaluation model in a critical or supercritical state of the high-pressure turbine is constructed according to a linear relation between a rotor axial force value in a critical or supercritical state of the high-pressure turbine and total pressure of an outlet of a gas compressor, and the axial force of a high-pressure turbine rotor of a platform is calculated in real time; in the constructed high-pressure turbine rotor axial force evaluation model, the influence of the total temperature of the outlet of the gas compressor and the rotating speed of the high-pressure turbine rotor on the axial force is also considered, the temperature correction coefficient and the rotating speed correction coefficient are adopted to correct the axial force value of the high-pressure turbine rotor in real time, the pneumatic essential characteristics contained in the axial force of the high-pressure turbine rotor are more met, the accuracy of the real-time calculation of the axial force of the high-pressure turbine rotor is improved, and technical support is provided for scientific research test safety and the convergence of the complete machine rotor axial force iterative design result.

Description

Real-time evaluation method and device for axial force of high-pressure turbine rotor
Technical Field
The invention relates to the technical field of aeroengines, and discloses a method and a device for evaluating axial force of a high-pressure turbine rotor in real time.
Background
In an aeroengine, the high-pressure turbine rotor axial force refers to turbine rotor runner axial force, and specifically comprises: the axial force of the blade body, the blade tip and the interstage disc cavity is three parts. The high-pressure turbine has very complex structure, extremely harsh working environment, and typical characteristics of high temperature, high pressure, high load and the like; in the whole machine environment, the inlet and outlet sections of the high-pressure turbine are difficult to arrange the flow passage pneumatic parameter measuring points, so that the axial force of the rotor of the high-pressure turbine is a technical difficulty in calculating the axial force of the whole machine.
In the aspect of real-time calculation of axial force of a rack turbine rotor, a real-time calculation method of axial force of a low-pressure turbine rotor of an aviation turbofan engine is provided by a patent CN 202210369066.2. Although this method is relatively simple in calculation process, it is not applicable to high pressure turbine rotor axial force calculation mainly because turbine outlet total pressure parameters are required in calculating turbine rotor axial force, but in an engine, the high pressure turbine rotor outlet is usually free of total pressure measurement points due to limited structural space and extremely harsh working environment of the high pressure turbine, and therefore the patent method is not applicable to calculating high pressure turbine rotor axial force.
Disclosure of Invention
The invention aims to provide a method and a device for evaluating the axial force of a high-pressure turbine rotor in real time, which can improve the accuracy of the real-time calculation of the axial force of the high-pressure turbine rotor.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a method for real-time assessment of high pressure turbine rotor axial force, comprising:
according to the inlet total temperature, inlet total pressure, outlet total temperature, outlet total pressure and flow of the high-pressure turbine at the design point, solving a rotor axial force simulation value of the high-pressure turbine at the design point through fluid simulation software;
by total pressure of outlet of air compressor
Figure SMS_1
Is an independent variable according to the formula->
Figure SMS_4
Constructing a rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, wherein +.>
Figure SMS_6
Rotor axial force simulation value for high-pressure turbine at design point, < >>
Figure SMS_2
Total compressor outlet pressure at design point for high-pressure turbine,/->
Figure SMS_5
Is a temperature correction coefficient>
Figure SMS_7
The value range is 0.9-1.1 #>
Figure SMS_8
For the rotational speed correction factor, < >>
Figure SMS_3
The value range is 0.9-1.05;
substituting the total compaction limit value of the outlet of the compressor in the state to be detected in the critical or supercritical state of the high-pressure turbine into the rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, and calculating the rotor axial force of the high-pressure turbine in the state to be detected.
Further, the temperature correction coefficient is according to the formula
Figure SMS_11
Calculated, wherein
Figure SMS_13
Is the air entraining coefficient of the flow of the air compressor, +.>
Figure SMS_16
For the air inlet mass flow of the compressor in the state to be tested, < + >>
Figure SMS_9
Is the constant pressure specific heat capacity of the air,
Figure SMS_12
is the total temperature of the outlet of the compressor in the state to be measured, +.>
Figure SMS_15
For the combustion efficiency of the combustion chamber>
Figure SMS_17
For the fuel mass flow in the state to be measured, < > for>
Figure SMS_10
Is the low calorific value of fuel>
Figure SMS_14
Is the constant pressure specific heat capacity of fuel gas +.>
Figure SMS_18
The total temperature of the combustion chamber outlet at the design point of the engine. />
Further, the rotational speed correction coefficient is according to the formula
Figure SMS_19
Calculated (obtained) by (I)>
Figure SMS_20
For the high-pressure turbine speed in the state to be measured, +.>
Figure SMS_21
The high pressure turbine speed is the design point.
In order to achieve the technical effects, the invention also provides a real-time evaluation device for axial force of a high-pressure turbine rotor, which comprises:
the simulation calculation module is used for solving a rotor axial force simulation value of the high-pressure turbine at a design point through fluid simulation software according to the inlet total temperature, the inlet total pressure, the outlet total temperature, the outlet total pressure and the flow of the high-pressure turbine at the design point;
an axial force evaluation model building module for using the total pressure of the outlet of the compressor
Figure SMS_24
As an independent variable according to the formula
Figure SMS_26
Constructing a rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, wherein +.>
Figure SMS_28
Rotor axial force simulation value for high-pressure turbine at design point, < >>
Figure SMS_23
Total compressor outlet pressure at design point for high-pressure turbine,/->
Figure SMS_25
Is a temperature correction coefficient>
Figure SMS_27
The value range is 0.9-1.1 #>
Figure SMS_29
For the rotational speed correction factor, < >>
Figure SMS_22
The value range is 0.9-1.05;
and the analysis module is used for substituting the total compaction limit value of the compressor outlet under the state to be tested in the critical or supercritical state of the high-pressure turbine into the rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, and calculating the rotor axial force of the high-pressure turbine under the state to be tested.
Further, the temperature correction coefficient in the axial force evaluation model building module is according to the formula
Figure SMS_30
Calculated, wherein->
Figure SMS_33
Is the air entraining coefficient of the flow of the air compressor, +.>
Figure SMS_38
For the air inlet mass flow of the compressor in the state to be tested, < + >>
Figure SMS_31
Is the constant pressure specific heat capacity of air +.>
Figure SMS_34
Is the total temperature of the outlet of the compressor in the state to be measured, +.>
Figure SMS_37
For the combustion efficiency of the combustion chamber>
Figure SMS_39
For the fuel mass flow in the state to be measured, < > for>
Figure SMS_32
Is the low calorific value of fuel>
Figure SMS_35
Is the constant pressure specific heat capacity of the fuel gas,
Figure SMS_36
the total temperature of the combustion chamber outlet at the design point of the engine.
Further, the rotational speed correction coefficient in the axial force evaluation model building module is according to the formula
Figure SMS_40
Calculated (obtained) by (I)>
Figure SMS_41
For the high-pressure turbine speed in the state to be measured, +.>
Figure SMS_42
The high pressure turbine speed is the design point.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the linear relation between the axial force value of the high-pressure turbine rotor and the total pressure of the outlet of the gas compressor when the high-pressure turbine is in critical or supercritical state, a high-pressure turbine rotor axial force evaluation model is constructed, and the axial force of the high-pressure turbine rotor of the rack is calculated in real time; in the constructed high-pressure turbine rotor axial force evaluation model, the influence of the total temperature of the outlet of the gas compressor and the rotating speed of the high-pressure turbine rotor on the axial force is also considered, the temperature correction coefficient and the rotating speed correction coefficient are adopted to correct the axial force value of the high-pressure turbine rotor in real time, the pneumatic essential characteristics contained in the axial force of the high-pressure turbine rotor are more met, the accuracy of the real-time calculation of the axial force of the high-pressure turbine rotor is improved, and technical support is provided for scientific research test safety and the convergence of the axial force iterative design result of the whole machine rotor;
2. when the high-pressure turbine reaches critical or supercritical, the axial force of the high-pressure turbine rotor of the rack can be calculated in real time only by the total pressure of the outlet of the gas compressor, and when the axial force of the high-pressure turbine rotor is calculated, the required test parameters are few;
3. because the total pressure of the outlet of the gas compressor is a parameter required by the performance judgment and control of the engine, the axial force evaluation method of the high-pressure turbine rotor can calculate the axial force of the high-pressure turbine rotor of the rack in real time under various test state conditions, especially under the condition that most rack test parameters of the engine are cancelled.
Drawings
FIG. 1 is a flow chart of a method for real-time assessment of high pressure turbine rotor axial force in an embodiment.
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.
Examples
Referring to fig. 1, a method for real-time assessment of high pressure turbine rotor axial force includes:
according to the inlet total temperature, inlet total pressure, outlet total temperature, outlet total pressure and flow of the high-pressure turbine at the design point, solving a rotor axial force simulation value of the high-pressure turbine at the design point through fluid simulation software;
by total pressure of outlet of air compressor
Figure SMS_45
Is an independent variable according to the formula->
Figure SMS_48
Constructing a rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, wherein +.>
Figure SMS_50
Rotor axial force simulation value for high-pressure turbine at design point, < >>
Figure SMS_43
Total compressor outlet pressure at design point for high-pressure turbine,/->
Figure SMS_46
Is a temperature correction coefficient>
Figure SMS_47
The value range is 0.9-1.1 #>
Figure SMS_49
For the rotational speed correction factor, < >>
Figure SMS_44
The value range is 0.9-1.05;
substituting the total compaction limit value of the outlet of the compressor in the state to be detected in the critical or supercritical state of the high-pressure turbine into the rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, and calculating the rotor axial force of the high-pressure turbine in the state to be detected.
In this embodiment, the high pressure turbine rotor may be pneumatically operated in response to the high pressure turbine rotor before it reaches a critical levelCharacteristic and total pressure of outlet of gas compressor for solving axial force of high-pressure turbine rotor
Figure SMS_53
Calculation of>
Figure SMS_55
For high pressure turbine rotor blade axial forces,
Figure SMS_59
，/>
Figure SMS_54
for high-pressure turbine rotor blade tip axial force +.>
Figure SMS_57
/2，/>
Figure SMS_58
Inlet flow for high pressure turbine before critical, +.>
Figure SMS_60
For the axial speed of the air flow of the inlet section of the high-pressure turbine rotor,/->
Figure SMS_52
For the axial speed of the air flow at the outlet section of the high-pressure turbine rotor,/->
Figure SMS_56
Static pressure of air flow at inlet section of high-pressure turbine rotor, < >>
Figure SMS_61
Static pressure of air flow at outlet section of high-pressure turbine rotor, < >>
Figure SMS_63
For the inlet area of the high-pressure turbine rotor blade, +.>
Figure SMS_51
For the outlet area of the high-pressure turbine rotor blade, +.>
Figure SMS_62
Is the tip area of the high pressure turbine rotor blade. When the high-pressure turbine reaches a critical value, the axial force value of the high-pressure turbine rotor after the design point state reaches the critical rotation speed is solved by utilizing fluid simulation software by acquiring relevant aerodynamic parameters of the high-pressure turbine in the design point state, then a high-pressure turbine rotor axial force evaluation model after the critical rotation speed is constructed according to the linear relation between the axial force value of the high-pressure turbine rotor after the critical rotation speed and the total pressure of an outlet of a gas compressor, and the axial force of the high-pressure turbine rotor of the gantry is calculated in real time; in the constructed high-pressure turbine rotor axial force evaluation model, the influence of the total temperature of the outlet of the gas compressor and the rotating speed of the high-pressure turbine rotor on the axial force is also considered, the temperature correction coefficient and the rotating speed correction coefficient are adopted to correct the axial force value of the high-pressure turbine rotor in real time, the pneumatic essential characteristics contained in the axial force of the high-pressure turbine rotor are more met, the accuracy of the real-time calculation of the axial force of the high-pressure turbine rotor is improved, and technical support is provided for scientific research test safety and the convergence of the complete machine rotor axial force iterative design result.
Based on the same inventive concept, the embodiment also provides a high-pressure turbine rotor axial force real-time evaluation device, which comprises:
the simulation calculation module is used for solving a rotor axial force simulation value of the high-pressure turbine at a design point through fluid simulation software according to the inlet total temperature, the inlet total pressure, the outlet total temperature, the outlet total pressure and the flow of the high-pressure turbine at the design point;
an axial force evaluation model building module for using the total pressure of the outlet of the compressor
Figure SMS_78
Is an independent variable according to the formula->
Figure SMS_67
Constructing a rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, wherein +.>
Figure SMS_70
Rotor axial force simulation value for high-pressure turbine at design point, < >>
Figure SMS_80
Total compressor outlet pressure at design point for high-pressure turbine,/->
Figure SMS_82
Is a temperature correction coefficient>
Figure SMS_81
The value range is 0.9-1.1 #>
Figure SMS_84
For the rotational speed correction factor, < >>
Figure SMS_73
The value range is 0.9-1.05; the temperature correction coefficient in this embodiment is according to the formula +.>
Figure SMS_76
Calculated, wherein->
Figure SMS_64
Is the air entraining coefficient of the flow of the air compressor, +.>
Figure SMS_69
For the air inlet mass flow of the compressor in the state to be tested, < + >>
Figure SMS_66
Is the constant pressure specific heat capacity of air +.>
Figure SMS_71
Is the total temperature of the outlet of the compressor in the state to be measured, +.>
Figure SMS_74
For the combustion efficiency of the combustion chamber>
Figure SMS_77
For the fuel mass flow in the state to be measured, < > for>
Figure SMS_72
Is the low calorific value of fuel>
Figure SMS_75
Constant pressure specific heat for fuel gasHold, fill (L)>
Figure SMS_79
The total temperature of the combustion chamber outlet at the design point of the engine. The rotational speed correction factor is->
Figure SMS_83
Calculated (obtained) by (I)>
Figure SMS_65
For the high-pressure turbine speed in the state to be measured, +.>
Figure SMS_68
The high pressure turbine speed is the design point.
And the analysis module is used for substituting the total compaction limit value of the compressor outlet under the state to be tested in the critical or supercritical state of the high-pressure turbine into the rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, and calculating the rotor axial force of the high-pressure turbine under the state to be tested.
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 (6)

1. A method for real-time assessment of axial force of a high pressure turbine rotor, comprising:
according to the inlet total temperature, inlet total pressure, outlet total temperature, outlet total pressure and flow of the high-pressure turbine at the design point, solving a rotor axial force simulation value of the high-pressure turbine at the design point through fluid simulation software;
by total pressure of outlet of air compressor
Figure QLYQS_3
Is an independent variable according to the formula->
Figure QLYQS_4
Constructing a rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, wherein +.>
Figure QLYQS_6
Rotor axial force simulation value for high-pressure turbine at design point, < >>
Figure QLYQS_1
Total compressor outlet pressure at design point for high-pressure turbine,/->
Figure QLYQS_5
Is a temperature correction coefficient>
Figure QLYQS_7
The value range is 0.9-1.1 #>
Figure QLYQS_8
For the rotational speed correction factor, < >>
Figure QLYQS_2
The value range is 0.9-1.05;
substituting the total compaction limit value of the outlet of the compressor in the state to be detected in the critical or supercritical state of the high-pressure turbine into the rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, and calculating the rotor axial force of the high-pressure turbine in the state to be detected.
2. The method for real-time assessment of high pressure turbine rotor axial force according to claim 1, wherein the temperature correction coefficient is according to the formula
Figure QLYQS_11
Calculated, wherein->
Figure QLYQS_14
Is the air entraining coefficient of the flow of the air compressor,
Figure QLYQS_17
for the air inlet mass flow of the compressor in the state to be tested, < + >>
Figure QLYQS_10
Is the constant pressure specific heat capacity of air +.>
Figure QLYQS_13
Is the total temperature of the outlet of the compressor in the state to be measured, +.>
Figure QLYQS_15
For the combustion efficiency of the combustion chamber>
Figure QLYQS_18
For the fuel mass flow in the state to be measured, < > for>
Figure QLYQS_9
Is the low calorific value of fuel>
Figure QLYQS_12
Is the constant pressure specific heat capacity of fuel gas +.>
Figure QLYQS_16
The total temperature of the combustion chamber outlet at the design point of the engine.
3. The method for real-time assessment of axial force of a high pressure turbine rotor of claim 1, wherein the rotational speed correction factor is according to the formula
Figure QLYQS_19
Calculated (obtained) by (I)>
Figure QLYQS_20
For the high-pressure turbine speed in the state to be measured, +.>
Figure QLYQS_21
The high pressure turbine speed is the design point.
4. A high pressure turbine rotor axial force real-time assessment device, comprising:
the simulation calculation module is used for solving a rotor axial force simulation value of the high-pressure turbine at a design point through fluid simulation software according to the inlet total temperature, the inlet total pressure, the outlet total temperature, the outlet total pressure and the flow of the high-pressure turbine at the design point;
an axial force evaluation model building module for using the total pressure of the outlet of the compressor
Figure QLYQS_24
As an independent variable according to the formula
Figure QLYQS_25
Constructing a rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, wherein +.>
Figure QLYQS_28
Rotor axial force simulation value for high-pressure turbine at design point, < >>
Figure QLYQS_23
Total compressor outlet pressure at design point for high-pressure turbine,/->
Figure QLYQS_26
Is a temperature correction coefficient>
Figure QLYQS_27
The value range is 0.9-1.1 #>
Figure QLYQS_29
For the rotational speed correction factor, < >>
Figure QLYQS_22
The value range is 0.9-1.05;
and the analysis module is used for substituting the total compaction limit value of the compressor outlet under the state to be tested in the critical or supercritical state of the high-pressure turbine into the rotor axial force evaluation model in the critical or supercritical state of the high-pressure turbine, and calculating the rotor axial force of the high-pressure turbine under the state to be tested.
5. The high pressure turbine rotor axial force real-time assessment device according to claim 4, which isCharacterized in that the temperature correction coefficient in the axial force evaluation model construction module is according to the formula
Figure QLYQS_31
Calculated, wherein->
Figure QLYQS_35
Is the air entraining coefficient of the flow of the air compressor, +.>
Figure QLYQS_38
For the air inlet mass flow of the compressor in the state to be tested, < + >>
Figure QLYQS_30
Is the constant pressure specific heat capacity of air +.>
Figure QLYQS_33
Is the total temperature of the outlet of the compressor in the state to be measured, +.>
Figure QLYQS_36
For the combustion efficiency of the combustion chamber>
Figure QLYQS_39
For the mass flow rate of the fuel in the state to be measured,
Figure QLYQS_32
is the low calorific value of fuel>
Figure QLYQS_34
Is the constant pressure specific heat capacity of fuel gas +.>
Figure QLYQS_37
The total temperature of the combustion chamber outlet at the design point of the engine. />
6. The apparatus of claim 4, wherein the rotational speed correction factor in the axial force assessment model building block is according to the formula
Figure QLYQS_40
Calculated (obtained) by (I)>
Figure QLYQS_41
For the high-pressure turbine speed in the state to be measured, +.>
Figure QLYQS_42
The high pressure turbine speed is the design point. />
CN202310466068.8A 2023-04-27 2023-04-27 Real-time evaluation method and device for axial force of high-pressure turbine rotor Active CN116205007B (en)

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Publication number Priority date Publication date Assignee Title
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US20210209264A1 (en) * 2020-01-02 2021-07-08 Viettel Group Modeling and calculation aerodynamic performances of multi-stage transonic axial compressors
CN114692309A (en) * 2022-04-08 2022-07-01 中国航发沈阳发动机研究所 Real-time calculation method for axial force of low-pressure turbine rotor of aviation turbofan engine
CN115618680A (en) * 2022-11-03 2023-01-17 成都中科翼能科技有限公司 Rapid numerical calculation method for axial force of rotor

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