CN112432793A - Gas turbine wheel disc air extraction test piece and modeling test parameter design method - Google Patents

Gas turbine wheel disc air extraction test piece and modeling test parameter design method Download PDF

Info

Publication number
CN112432793A
CN112432793A CN202011318613.1A CN202011318613A CN112432793A CN 112432793 A CN112432793 A CN 112432793A CN 202011318613 A CN202011318613 A CN 202011318613A CN 112432793 A CN112432793 A CN 112432793A
Authority
CN
China
Prior art keywords
wheel disc
test
modeling
air
test piece
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
CN202011318613.1A
Other languages
Chinese (zh)
Inventor
苏鹏飞
赵世全
孔祥林
周娜
卢航
蔡国煌
罗涛
李金鸿
尹正发
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.)
DEC Dongfang Turbine Co Ltd
Original Assignee
DEC Dongfang Turbine Co Ltd
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 DEC Dongfang Turbine Co Ltd filed Critical DEC Dongfang Turbine Co Ltd
Priority to CN202011318613.1A priority Critical patent/CN112432793A/en
Publication of CN112432793A publication Critical patent/CN112432793A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/02—Details or accessories of testing apparatus
    • 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
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • Fluid Mechanics (AREA)
  • Mathematical Physics (AREA)
  • Computing Systems (AREA)
  • Algebra (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Computational Mathematics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

The invention discloses a gas turbine wheel disc air extraction test piece, which comprises a wheel disc part A, a wheel disc part B and a wheel disc part C, wherein the wheel disc part A is provided with a first air inlet and a second air inlet; the side, close to each other, of the wheel disc part B and the wheel disc part C forms an air inlet cavity, and the wheel disc part B is provided with an air suction hole and a channel B; the wheel disc part C is provided with a central hole C; the modeling test parameter design method comprises obtaining similarity criterion of wheel disc air-extraction rotation modeling test; determining a modeling ratio; calculating the diameter of a modeling test model, the diameter of a central hole of a modeling test wheel disc air exhaust test piece, the diameter of an air exhaust hole of the modeling test wheel disc air exhaust test piece, the size of a gap of the modeling test wheel disc air exhaust test piece, the mass flow of compressed air in a modeling test, the total pressure of inlet gas in the modeling test, the static pressure of outlet gas in the modeling test and the rotating speed of a rotor in the modeling test. The method can obtain real and reliable key pneumatic parameters of the cold air conveying section of the gas turbine rotor, and can check and improve the conventional theoretical calculation model by using the test result.

Description

Gas turbine wheel disc air extraction test piece and modeling test parameter design method
Technical Field
The invention relates to the technical field of gas turbine wheel disc air extraction test pieces, in particular to a gas turbine wheel disc air extraction test piece and a modeling test parameter design method.
Background
An effective method for improving the cycle efficiency of the gas turbine is to improve the gas inlet temperature of the gas turbine, wherein the wheel disc of the gas turbine compressor section performs air extraction to provide cooling gas for high-temperature blades of the turbine, so that the cooling of an air extraction test piece of the wheel disc of the turbine and the sealing of a wheel rim are realized, main stream gas is prevented from flowing backwards, and the heat efficiency and the operation safety of the gas turbine are greatly influenced.
The prior art and published literature reports still have blank for gas turbine wheel disc air extraction modeling test devices and test methods. Key parameters of the cooling gas, such as pressure loss in the wheel disc bleed test piece gap, are critical throughout the wheel disc bleed molding flow path, and these critical parameters determine the pressure, flow rate and temperature of the cooling gas supply.
A plurality of numerical simulation calculation and calculation results for one-dimensional, two-dimensional and three-dimensional numerical simulation calculation and calculation results of a gas turbine cooling gas supply system are published at present, and obvious differences exist in calculation results of key structures such as the gap pressure loss of a wheel disc air extraction test piece by different calculation methods through comparing the existing numerical calculation results.
Disclosure of Invention
The invention aims to solve the technical problem of providing a gas turbine wheel disc air extraction test piece and a modeling test parameter design method, which can effectively obtain real and reliable key pneumatic parameters of a gas turbine rotor cold air conveying section and can check and improve the conventional theoretical calculation model by using a test result.
The technical problem to be solved by the invention is as follows:
on one hand, the gas turbine wheel disc air extraction test piece comprises a wheel disc part A, a wheel disc part B and a wheel disc part C which are sequentially connected and coaxially arranged; the side, close to each other, of the wheel disc part B and the wheel disc part C form an air inlet cavity, an air suction hole communicated with the air inlet cavity and a channel B communicated with one end, far away from the air inlet cavity, of the air suction hole are arranged on the wheel disc part B, and a central hole C coaxial with and communicated with the channel B is arranged on the wheel disc part C; the air inlet cavity, the air suction hole, the channel B and the central hole C form an air circulation channel.
In some possible embodiments, the passage B includes a chamber a communicating with the suction hole, a center hole B coaxial with and communicating with the chamber a, the chamber a being provided on a side of the wheel disc element B close to the wheel disc element a, the center hole B corresponding to a diameter of the center hole C; the wheel disc component A, the wheel disc component B and the wheel disc component C are disc-shaped and coaxial, and the central hole B and the central hole C are coaxially arranged with the wheel disc component A.
In some possible embodiments, the number of the pumping holes is multiple, and the pumping holes are arranged in an annular array with the center of the chamber a as a center.
In some possible embodiments, the wheel element a is provided with mounting holes, and the mounting holes are coaxial with the central holes B and C.
In some possible embodiments, in order to achieve a variation of the shape of the chamber a, in turn simulating the structure of a real chamber a; one side of the wheel disc component A, which is close to the wheel disc component B, is provided with a mounting cavity communicated with the mounting hole, the test piece further comprises a shaft end nut, and a cavity A is formed in one side of the shaft end nut, which is close to the wheel disc component B.
In some possible embodiments, in order to effectively realize the gas inlet, the gas inlet cavity comprises a groove C which is arranged on one side of the wheel disc component C close to the wheel disc component B and is in a circular ring shape, and a gap C which is arranged between the wheel disc component B and the wheel disc component C and is used for conveying the gas to the communication of the groove C.
On the other hand, the design method of the gas turbine wheel disc air extraction modeling test parameters specifically comprises the following steps:
obtaining the similar criterion of the wheel disc air extraction rotation modeling test:
determining the modeling ratio of the test;
calculating the diameter of a modeling test model, the diameter of a center hole of a modeling test wheel disc air-extracting test piece, the diameter of an air-extracting hole of the modeling test wheel disc air-extracting test piece, the size of a gap of the modeling test wheel disc air-extracting test piece, the mass flow of compressed air in the modeling test, the total pressure of inlet gas in the modeling test, the static pressure of outlet gas in the modeling test and the rotating speed of a rotor in the modeling test.
In some possible embodiments, the obtaining of the criterion of the similarity criterion of the disk pumping rotational modeling test specifically includes:
performing modeling treatment by using a similar theory, wherein the original model flow and the test model flow meet the same fluid control equation, and the corresponding dimensionless criterion numbers are equal; from the formula of fluid mechanics, the following formula of criteria numbers can be obtained:
Figure BDA0002792095500000021
in the formula: maRepresenting gas turbine compressed air mach number;
v represents gas turbine airflow velocity;
gamma represents a gas adiabatic factor, which is constant;
r represents a gas molar constant;
t represents the outside air temperature;
d represents a characteristic length;
v represents the kinematic viscosity of the gas;
re represents the gas turbine airflow Reynolds number;
Rerrepresenting the gas turbine airflow rotation Reynolds number;
ω represents gas turbine airflow rotation angular velocity;
according to the similarity criterion, when the three criteria are equal in number,
Figure BDA0002792095500000039
Figure BDA0002792095500000031
equal, Ps＝ρRTSThe following dimensionless criterion numbers can be derived:
dimensionless flow:
Figure BDA0002792095500000032
reynolds number:
Figure BDA0002792095500000033
reynolds number of rotation:
Figure BDA0002792095500000034
kinetic viscosity was calculated using the formula of asiatland:
Figure BDA0002792095500000035
the similar criterion of the gas turbine wheel disc air extraction rotation modeling test can be written by the formula:
Figure BDA0002792095500000036
Figure BDA0002792095500000037
Figure BDA0002792095500000038
in the formula: m represents the compressed air mass flow;
Figure BDA00027920955000000310
represents the compressed air density;
v represents the test gas flow rate;
a represents the test flow area;
Ttrepresents the total temperature of the test gas;
Tsrepresents the static temperature of the test gas;
Ptrepresents the total pressure of the test gas;
Psrepresents static pressure;
μ represents kinematic viscosity;
the meaning of the characters in the similar criteria formulas (1), (2) and (3) is similar to that described above, and the subscript 1 and the subscript 2 are only used for distinguishing the actual value from the modeled value;
in some possible embodiments, the calculating the modeled test model diameter specifically includes:
Dm＝D*C；
in the formula: d represents the model diameter under the design working condition;
c represents the modeling ratio of the test;
Dmthe modeled test model diameter is indicated.
In some possible embodiments, the calculating the diameter of the central hole of the air suction test piece of the modeled test wheel disc is that the central hole is a central hole B or a central hole C, and specifically:
Dc,m＝Dc*C；
in the formula: dcThe diameter of a central hole of a wheel disc air suction test piece under a design working condition is shown; dc,mThe diameter of the central hole of the air suction test piece of the modeling test wheel disc is shown.
In some possible embodiments, the calculating a modeled test wheel disc extraction test piece extraction hole diameter is according to the formula:
Dl,m＝Dl*C；
in the formula: dlThe diameter of an air suction hole of a wheel disc air suction test piece under a design working condition is shown; dl,mAnd the diameter of an air suction hole of an air suction test piece of the modeling test wheel disc is shown.
In some possible embodiments, the calculating the size of the clearance C in the modeled test wheel disc suction test piece is specifically:
Lm＝L*C；
in the formula: l represents the size of a gap C in the wheel disc air suction test piece under the design working condition; l ismThe gap C size in the modeled test wheel disc suction test piece is shown.
In some possible embodiments, the calculating the compressed air mass flow rate in the modeling test specifically includes:
Figure BDA0002792095500000051
in some possible embodiments, the total pressure of the inlet gas in the modeling test is calculated by the formula:
Figure BDA0002792095500000052
in some possible embodiments, according to P before and after modellingt/PsThe outlet gas static pressure is calculated to be equal.
In some possible embodiments, the calculating the rotor speed in the modeling test specifically includes:
Figure BDA0002792095500000053
compared with the prior art, the invention has the beneficial effects that:
the invention can fix the test variable of compressed air to the normal temperature state after the molding treatment, so that a temperature changing device of the compressed air is not needed at the air inlet system part, the test steps are simplified, and the test efficiency is improved.
The method can obtain real and reliable key pneumatic parameters of the cold air conveying section of the gas turbine rotor, and can check and improve the conventional theoretical calculation model by using the test result;
the technical parameters of the key structure can be obtained through the clearance modeling test of the gas turbine wheel disc air extraction test piece, and the existing calculation tool is checked and improved, so that the method has important significance for the design of the gas turbine;
the invention effectively realizes the modeling rotation test of the gas turbine wheel disc air extraction, can perform modeling tests of different sizes through different modeling treatments, and can use normal temperature air as a gas working medium after the modeling treatments, thereby greatly improving the efficiency of the gas turbine wheel disc air extraction rotation test.
Drawings
FIG. 1 is a schematic view of the connection relationship of the wheel disc air suction test piece in the present invention;
wherein: 1. a rotor shaft; 2. an exhaust funnel; 31. a wheel element B; 311. an air exhaust hole; 312. a chamber A; 32. a wheel element A; 321. a shaft end nut; 33. a wheel element C; 331. a groove C; 332. and a gap C.
Detailed Description
To make the purpose, technical solutions and advantages of the present application clearer, the technical solutions in the present application will be clearly and completely described below with reference to the drawings in the present application, and it is obvious that the described embodiments are some, but not all embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the implementation of the present application, "and/or" describes an association relationship of associated objects, which means that there may be three relationships, for example, a and/or B, which may mean: a exists alone, A and B exist simultaneously, and B exists alone.
The invention is further illustrated with reference to the following figures and examples.
The invention is realized by the following technical scheme, as shown in figure 1,
on the one hand, the gas turbine wheel disc air extraction test piece comprises a wheel disc part A32, a wheel disc part B31 and a wheel disc part C33 which are sequentially connected and coaxially arranged; the side, close to each other, of the wheel disc part B31 and the wheel disc part C33 form an air inlet cavity, the wheel disc part B31 is provided with an air suction hole 311 communicated with the air inlet cavity and a channel B communicated with one end, far away from the air inlet cavity, of the air suction hole 311, and the wheel disc part C33 is provided with a center hole C coaxial and communicated with the channel B; the air inlet cavity, the air pumping hole 311, the channel B and the central hole C form an air circulation channel.
Gas enters the pumping hole 311 from the gas inlet cavity, then enters the central hole C through the channel B, and is discharged from the central hole C; the flow characteristic parameters of a key structure in the air extraction of the gas turbine compressor wheel disc are tested by matching with a rotation test device, real and reliable performance parameters of the air extraction section of the gas turbine compressor wheel disc are obtained, important data support can be provided for the design of a gas turbine, and the checking and the correction can be performed on the existing one-dimensional, two-dimensional and three-dimensional calculation models aiming at the secondary air system of the gas turbine.
In some possible embodiments, the passage B includes a chamber a312 communicating with the suction hole 311, a center hole B coaxial with and communicating with the chamber a312, the chamber a312 being provided on a side of the wheel element B31 close to the wheel element a32, the center hole B corresponding to a diameter of the center hole C; the wheel element a32, the wheel element B31, and the wheel element C33 are disc-shaped, and the axis of the center hole B or the center hole C is coaxial with the center of the wheel element a32, the wheel element B31, or the wheel element C33.
The chamber A312 is a communicating chamber between the pumping hole 311 and the central hole B; it can be adjusted according to the real chamber structure;
in some possible embodiments, to achieve a change in the shape of the chamber a312, thereby simulating the structure of the real chamber a 312; one side of the wheel disc component A32, which is close to the wheel disc component B31, is provided with a mounting cavity communicated with the mounting hole, the test piece further comprises an axial end nut 321, and one side of the axial end nut 321, which is close to the wheel disc component B31, forms a cavity A312.
Preferably, the shape of the shaft end nut 321 can be adjusted according to the requirement of the cavity a312, so as to simulate the structure of the real cavity a 312.
In some possible embodiments, the plurality of pumping holes 311 are arranged in an annular array around the center of the chamber a312, that is, the pumping holes are circumferentially distributed on the wheel disc B31 around the central axis of the chamber a 312.
In some possible embodiments, in order to realize the connection between the test piece and the rotor shaft in the rotation test device, the wheel disc part a32 is provided with mounting holes which are coaxial with the central holes B and C.
In some possible embodiments, the intake chamber includes a groove C331 provided in a circular ring shape on a side of the wheel element C33 close to the wheel element B31, and a gap C332 provided between the wheel element B31 and the wheel element C33 and communicating with the groove C331 for delivering gas.
Preferably, the opening of the recess C331 is provided on the side close to the wheel element B31, and forms a chamber with the side of the wheel element B31, the chamber communicating with the clearance C332, thereby achieving the gas entering from the outside into the chamber, and entering into the chamber a312 through the suction hole 311, and then being discharged through the center hole B and the center hole C.
Preferably, in order to ensure the stability of the test piece in the test process, the balancing weight is symmetrically installed on one side of the part A and the part C which are far away from each other, and the weight of the balancing weight is adjusted according to the requirement after the test piece is installed.
In some possible embodiments, in order to efficiently achieve positioning of the wheel element a32, the wheel element B31, the wheel element C33; and the wheel disc component C33 is provided with a positioning pin which penetrates through the wheel disc component A32 and the wheel disc component B31 and is installed on the wheel disc component A32.
Preferably, the pumping hole 311 is obliquely disposed and is respectively communicated with the recess C331 and the chamber a 312.
The rotation test device comprises a rotation device provided with a rotor shaft 1, a test box provided with an air seal piece and an air inlet system connected with the test box; wherein one end of the rotor shaft 1 extends into the test box; the wheel disc component A32 is mounted on the rotor shaft 1 through a mounting hole, the shaft end nut mounting 321 is mounted at the end part of the rotor shaft 1, and the connection of the wheel disc component A32, the wheel disc component B31 and the wheel disc component C33 is realized through bolts; the outer side of the exhaust pipe 2 is fixedly connected with a wheel element B31 and a wheel element C.
Preferably, the wheel element B31 and the wheel element C33 are provided with exhaust funnel mounting grooves coaxial with the center hole B; the inner diameter of the exhaust funnel 2 is consistent with the diameters of the central hole B and the central hole C.
To effect a change in the shape of chamber a312, the end surface of shaft end nut 321 and/or the end surface of exhaust stack 2 adjacent to shaft end nut 321 may be adjusted to effect a change in the configuration of chamber a 312.
Before the test, the wheel disc component A32 is installed on the rotor shaft 1, the connection of the wheel disc component A32 and the rotor shaft 1 is realized through a flat key, then a shaft end nut 321 is installed at the shaft end of the rotor shaft 1, the connection of the wheel disc component A32, the wheel disc component B31 and the wheel disc component C33 is realized through bolts, and the test piece is positioned in a test box after the installation is finished; during the experiment, realize the adjustment to the different rotational speeds of this test piece through control rotor shaft 1, air intake system is gaseous to the proof box interior input, and can be to the gaseous pressure in the input proof box, the flow is adjusted, gaseous entering air inlet cavity through clearance C, measuring transducer in the proof box will carry out the measurationwith pressure to the gaseous temperature in the proof box, then enter into cavity A through the aspirating hole, then through centre bore C, the aiutage discharges, it measures to exhaust gas's temperature pressure to have set up measuring transducer on the aiutage.
On the other hand, the design method of the gas turbine wheel disc air extraction modeling test parameters specifically comprises the following steps:
obtaining the similar criterion of the wheel disc air extraction rotation modeling test:
determining the modeling ratio of the test;
calculating the diameter of a modeling test model, the diameter of a center hole of a modeling test wheel disc air-extracting test piece, the diameter of an air-extracting hole of the modeling test wheel disc air-extracting test piece, the size of a gap of the modeling test wheel disc air-extracting test piece, the mass flow of compressed air in the modeling test, the total pressure of inlet gas in the modeling test, the static pressure of outlet gas in the modeling test and the rotating speed of a rotor in the modeling test.
The method comprises the steps of calculating the diameter of a modeling test model, the diameter of a central hole of a modeling test wheel disc air-extracting test piece, the diameter of an air-extracting hole of the modeling test wheel disc air-extracting test piece, the size of a gap of the modeling test wheel disc air-extracting test piece, the mass flow of compressed air in a modeling test, the total pressure of inlet gas in the modeling test, the static pressure of outlet gas in the modeling test and the rotating speed of a rotor in the modeling test; the method specifically comprises the following steps:
performing modeling treatment by using a similar theory, wherein the original model flow and the test model flow meet the same fluid control equation, and the corresponding dimensionless criterion numbers are equal; reynolds number of original model flow less than 3 x 105The viscous force is not negligible, the Mach number is greater than 0.3, the elastic force is not negligible, and the similar dimensionless criterion numbers all meet the condition that the dimensionless criterion numbers are equal when the test is subjected to modeling treatment; from the formula of fluid mechanics, the following formula of criteria numbers can be obtained:
Figure BDA0002792095500000081
in the formula: maRepresenting gas turbine compressed air mach number;
v represents gas turbine airflow velocity;
gamma represents a gas adiabatic factor;
r represents a gas molar constant;
t represents the outside air temperature;
d represents a characteristic length;
v represents the kinematic viscosity of the gas;
re represents the gas turbine airflow Reynolds number;
Rerrepresenting the gas turbine airflow rotation Reynolds number;
ω represents gas turbine airflow rotation angular velocity;
according to the similarity criterion, the three criteria are equal in number and
Figure BDA00027920955000000912
Figure BDA0002792095500000091
also equal, the following dimensionless criterion numbers can be deduced:
dimensionless flow:
Figure BDA0002792095500000092
reynolds number:
Figure BDA0002792095500000093
reynolds number of rotation:
Figure BDA0002792095500000094
wherein:
Figure BDA0002792095500000095
the derivation of (c) is as follows:
by
Figure BDA00027920955000000913
To obtain
Figure BDA0002792095500000096
The following can be obtained:
Figure BDA0002792095500000097
Figure BDA0002792095500000098
the derivation of (c) is as follows:
from Pt＝ρRTt，
Figure BDA0002792095500000099
The following can be obtained:
Figure BDA00027920955000000910
Figure BDA00027920955000000911
kinetic viscosity was calculated using the formula of asiatland:
Figure BDA0002792095500000101
the similar criterion of the gas turbine wheel disc air extraction rotation modeling test can be written by the formula:
Figure BDA0002792095500000102
Figure BDA0002792095500000103
Figure BDA0002792095500000104
in the formula: m represents the compressed air mass flow;
Figure BDA0002792095500000105
represents the compressed air density; v represents the test gas flow rate; a represents the test flow area; t istRepresents the total temperature of the test gas; t issRepresents the static temperature of the test gas; ptRepresents the total pressure of the test gas; psRepresents static pressure; μ represents kinematic viscosity;
the meaning of characters in the similar criteria formulas (1), (2) and (3) is similar to that of the characters in the formulas (1), (2) and (3), and the subscript 1 and the subscript 2 are only used for distinguishing an actual value from a modeled value;
the diameter of the model of the modeling test is calculated as follows:
Dm＝D*C；
in the formula: d represents the model diameter under the design working condition;
c represents the modeling ratio of the test;
Dmrepresenting the diameter of the modeling test model;
calculating the diameter of a central hole of a pumping test piece of the modular test wheel disc, wherein the central hole is a central hole B or a central hole C, and the method specifically comprises the following steps:
Dc,m＝Dc*C；
in the formula: dcThe diameter of a central hole of a wheel disc air suction test piece under a design working condition is shown; dc,mThe diameter of the central hole of the air suction test piece of the modeling test wheel disc is shown;
calculating the diameter of the air exhaust hole 311 of the air exhaust test piece of the modeling test wheel disc, wherein the formula is as follows:
Dl,m＝Dl*C；
in the formula: dlThe diameter of an air suction hole of a wheel disc air suction test piece under a design working condition is shown; dl,mThe diameter of an air suction test piece air suction hole 311 of the modeled test wheel disc is shown;
calculating the size of a gap C332 in the air exhaust test piece of the modular test wheel disc, and specifically:
Lm＝L*C；
in the formula: l represents the size of a gap C in the wheel disc air suction test piece under the design working condition; l ismIndicating the size of a clearance C332 in the air suction test piece of the modeling test wheel disc;
calculating the mass flow of compressed air in the modeling test, specifically comprising the following steps:
Figure BDA0002792095500000111
and (3) calculating the total pressure of the inlet gas in the modeling test, wherein the formula is as follows:
Figure BDA0002792095500000112
according to P before and after modellingt/PsCalculating the outlet gas static pressure in an equal way;
calculating the rotor rotating speed in the modeling test, specifically:
Figure BDA0002792095500000113
it should be noted that the modeling working condition of the wheel disc hole inclination angle is consistent with the design working condition, and the inlet temperature after modeling is selected to be the normal temperature environment for simplifying the test.
The modeling test of the gas turbine wheel disc air extraction is effectively realized, modeling tests with different sizes can be performed through different modeling treatments, and normal-temperature air can be used as a gas working medium in the gas turbine wheel disc air extraction rotation test device after the modeling treatments, so that the efficiency of the gas turbine wheel disc air extraction rotation test is greatly improved.
The foregoing detailed description of the embodiments of the present application has been presented, and specific examples have been applied in the present application to explain the principles and implementations of the present application, and the above description of the embodiments is only used to help understand the method and the core ideas of the present application; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and as described above, the content of the present specification should not be construed as a limitation to the present application.

Claims (10)

1. The utility model provides a gas turbine rim plate bleeding test piece which characterized in that: the wheel disc component comprises a wheel disc component A, a wheel disc component B and a wheel disc component C which are sequentially connected and coaxially arranged; the side, close to each other, of the wheel disc part B and the wheel disc part C form an air inlet cavity, the wheel disc part B is provided with an air suction hole communicated with the air inlet cavity and a channel B communicated with one end, far away from the air inlet cavity, of the air suction hole, and the wheel disc part C is provided with a central hole C coaxial with and communicated with the channel B; the air inlet cavity, the air suction hole, the channel B and the central hole C form a circulation channel.
2. The gas turbine disk extraction test piece of claim 1, wherein: the channel B comprises a cavity A communicated with the air suction hole and a central hole B coaxial and communicated with the cavity A, the cavity A is arranged on one side, close to the wheel disc part A, of the wheel disc part B, and the diameter of the central hole B is consistent with that of the central hole C; the wheel disc component A, the wheel disc component B and the wheel disc component C are disc-shaped and coaxial, and the central hole B and the central hole C are coaxially arranged with the wheel disc component A.
3. The gas turbine disk extraction test piece of claim 2, wherein: the number of the pumping holes is multiple, and the pumping holes are circumferentially distributed by taking the central axis of the cavity A as a center.
4. The gas turbine disk extraction test piece of claim 2, wherein: the wheel disc part A is provided with a mounting hole which is coaxial with the central hole B and the central hole C.
5. The gas turbine disk extraction test piece of claim 4, wherein: one side of the wheel disc component A, which is close to the wheel disc component B, is provided with a mounting cavity communicated with the mounting hole, the test piece further comprises a shaft end nut, and a cavity A is formed in one side of the shaft end nut, which is close to the wheel disc component B.
6. The gas turbine disk extraction test piece of claim 1, wherein: the air inlet cavity comprises a groove C which is arranged on one side of the wheel disc component C close to the wheel disc component B and is in a circular ring shape, and a gap C which is arranged between the wheel disc component B and the wheel disc component C and is used for conveying gas to the groove C.
7. A gas turbine wheel disc air extraction modeling test parameter design method is characterized by comprising the following steps: the gas turbine disk air extraction test piece applied to any one of claims 1 to 6, specifically comprising the following steps:
obtaining the similar criterion of the wheel disc air extraction modeling test:
determining the modeling ratio of the test;
calculating the diameter of a modeling test model, the diameter of a center hole of a modeling test wheel disc air-extracting test piece, the diameter of an air-extracting hole of the modeling test wheel disc air-extracting test piece, the size of a gap of the modeling test wheel disc air-extracting test piece, the mass flow of compressed air in the modeling test, the total pressure of inlet gas in the modeling test, the static pressure of outlet gas in the modeling test and the rotating speed of a rotor in the modeling test.
8. The method for designing the parameters of the gas turbine disk extraction modeling test of claim 7, wherein: the similar criterion for obtaining the wheel disc air extraction rotation modeling test specifically comprises the following steps:
performing modeling treatment by using a similar theory, wherein the original model flow and the test model flow meet the same fluid control equation, and the corresponding dimensionless criterion numbers are equal; from the formula of fluid mechanics, the following formula of criteria numbers can be obtained:
Figure FDA0002792095490000021
in the formula: maRepresenting gas turbine compressed air mach number; v represents gas turbine airflow velocity; gamma represents a gas adiabatic factor; r represents a gas molar constant; t represents the outside air temperature; d represents a characteristic length; v represents the kinematic viscosity of the gas; re represents the gas turbine airflow Reynolds number; rerRepresenting the gas turbine airflow rotation Reynolds number; ω represents gas turbine airflow rotation angular velocity;
according to the similarity criterion, the three criteria are equal in number and
Figure FDA00027920954900000211
Figure FDA0002792095490000022
equality, we derive the following dimensionless criterion numbers:
dimensionless flow:
Figure FDA0002792095490000023
reynolds number:
Figure FDA0002792095490000024
reynolds number of rotation:
Figure FDA0002792095490000025
kinetic viscosity was calculated using the formula of asiatland:
Figure FDA0002792095490000026
the similar criterion of the gas turbine wheel disc air extraction rotation modeling test can be written by the formula:
Figure FDA0002792095490000027
Figure FDA0002792095490000028
Figure FDA0002792095490000029
in the formula: m represents the compressed air mass flow;
Figure FDA00027920954900000210
represents the compressed air density; v represents the test gas flow rate; a represents the test flow area; t istRepresents the total temperature of the test gas; t issRepresents the static temperature of the test gas; ptIndicating testTotal pressure of the gas; psRepresents static pressure; μ represents kinematic viscosity;
the meaning of the characters in the similar criteria equations (1), (2), (3) is similar to that described above, and subscript 1 and subscript 2 are used only to distinguish actual values from modeled values.
9. The method for designing the parameters of the gas turbine disk extraction modeling test of claim 8, wherein: the diameter of the model of the modeling test is calculated, and the method specifically comprises the following steps:
Dm＝D*C；
in the formula: d represents the model diameter under the design working condition;
c represents the modeling ratio of the test;
Dmrepresenting the diameter of the modeling test model;
the diameter of a central hole of the air suction test piece of the modular test wheel disc is calculated, and the central hole is a central hole B or a central hole C; the method specifically comprises the following steps:
Dc,m＝Dc*C；
in the formula: dcThe diameter of a central hole of a wheel disc air suction test piece under a design working condition is shown; dc,mThe diameter of the central hole of the air suction test piece of the modeling test wheel disc is shown;
the diameter of the air exhaust hole of the air exhaust test piece of the modeling test wheel disc is calculated according to the formula:
Dl,m＝Dl*C；
in the formula: dlThe diameter of an air suction hole of a wheel disc air suction test piece under a design working condition is shown; dl,mThe diameter of an air suction hole of an air suction test piece of the modeling test wheel disc is shown;
the size of the gap C in the air exhaust test piece of the wheel disc of the modeling test is calculated and specifically comprises the following steps:
Lm＝L*C；
in the formula: l represents the size of a gap C in the wheel disc air suction test piece under the design working condition; l ismThe gap C size in the modeled test wheel disc suction test piece is shown.
10. The method for designing the parameters of the gas turbine disk extraction modeling test of claim 8, wherein: the compressed air mass flow in the calculation modeling test specifically comprises the following steps:
Figure FDA0002792095490000031
the total pressure of the inlet gas in the modeling test is calculated by the formula:
Figure FDA0002792095490000041
according to P before and after modellingt/PsCalculating the outlet gas static pressure in an equal way;
the method for calculating the rotor rotation speed in the modeling test specifically comprises the following steps:
Figure FDA0002792095490000042
CN202011318613.1A 2020-11-23 2020-11-23 Gas turbine wheel disc air extraction test piece and modeling test parameter design method Pending CN112432793A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011318613.1A CN112432793A (en) 2020-11-23 2020-11-23 Gas turbine wheel disc air extraction test piece and modeling test parameter design method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011318613.1A CN112432793A (en) 2020-11-23 2020-11-23 Gas turbine wheel disc air extraction test piece and modeling test parameter design method

Publications (1)

Publication Number Publication Date
CN112432793A true CN112432793A (en) 2021-03-02

Family

ID=74693521

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011318613.1A Pending CN112432793A (en) 2020-11-23 2020-11-23 Gas turbine wheel disc air extraction test piece and modeling test parameter design method

Country Status (1)

Country Link
CN (1) CN112432793A (en)

Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1209186A (en) * 1996-02-16 1999-02-24 株式会社日立制作所 Steam turbine power generating plant and steam turbine
CN1495351A (en) * 2002-06-06 2004-05-12 ŵ��Ƥ����ڿع����޹�˾ System for controlling and regulating rlame temp. of single shaft gas turbine
CN101230790A (en) * 2007-01-24 2008-07-30 通用电气公司 Control system based on forecasting model for heavy gas turbine
CN103423205A (en) * 2013-08-19 2013-12-04 浙江大学 Centrifugal degassing delivery pump
CN203403909U (en) * 2013-08-30 2014-01-22 哈尔滨汽轮机厂有限责任公司 Turbine body of gas turbine
CN204663669U (en) * 2015-03-27 2015-09-23 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Gas turbine rotor axial thrust balancing bleed structure
CN106017908A (en) * 2016-07-28 2016-10-12 上海发电设备成套设计研究院 Rotating turbine flow and cooling test device and method
CN107014618A (en) * 2017-03-29 2017-08-04 浙江大学 A kind of combustion chamber and turbine coupling mechanism experiment research device
CN207248535U (en) * 2017-08-30 2018-04-17 华能国际电力股份有限公司 Gas turbine blade end wall heat transfer test system
CN109139122A (en) * 2018-11-07 2019-01-04 哈尔滨电气股份有限公司 A kind of inner cooling system of 2 grades of turbine rotors of gas turbine
CN109812299A (en) * 2019-01-17 2019-05-28 杭州汽轮动力集团有限公司 A kind of gas turbine turbine rotor cooling means and cooling gas system
CN110069848A (en) * 2019-04-18 2019-07-30 西安交通大学 A kind of turbine blade is pneumatic-dehumidifying-cooling test modeling method
CN110132556A (en) * 2019-04-30 2019-08-16 中国航发湖南动力机械研究所 Modularization turbine test part and its test method
CN110261433A (en) * 2019-07-05 2019-09-20 西安交通大学 A kind of removal model experimental device of aviation gas turbine movable vane internal heat transfer
CN110700901A (en) * 2019-11-19 2020-01-17 中国特种设备检测研究院 Experimental device for be used for impeller machinery fault simulation and monitoring
CN110726540A (en) * 2019-10-11 2020-01-24 中国航发沈阳发动机研究所 Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar
CN110821883A (en) * 2019-12-04 2020-02-21 哈尔滨电气股份有限公司 Modularized compressor rotor applied to heavy gas turbine
CN111062124A (en) * 2019-12-05 2020-04-24 西安交通大学 Similar modeling method for supercritical carbon dioxide compressor test
CN111561356A (en) * 2020-05-20 2020-08-21 哈电发电设备国家工程研究中心有限公司 Be applied to heavy gas turbine's modularization turbine rotor
CN111735844A (en) * 2020-07-14 2020-10-02 西安交通大学 Experimental system and method for cooling test of front edge of turbine blade under rotation condition

Patent Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1209186A (en) * 1996-02-16 1999-02-24 株式会社日立制作所 Steam turbine power generating plant and steam turbine
CN1495351A (en) * 2002-06-06 2004-05-12 ŵ��Ƥ����ڿع����޹�˾ System for controlling and regulating rlame temp. of single shaft gas turbine
CN101230790A (en) * 2007-01-24 2008-07-30 通用电气公司 Control system based on forecasting model for heavy gas turbine
CN103423205A (en) * 2013-08-19 2013-12-04 浙江大学 Centrifugal degassing delivery pump
CN203403909U (en) * 2013-08-30 2014-01-22 哈尔滨汽轮机厂有限责任公司 Turbine body of gas turbine
CN204663669U (en) * 2015-03-27 2015-09-23 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Gas turbine rotor axial thrust balancing bleed structure
CN106017908A (en) * 2016-07-28 2016-10-12 上海发电设备成套设计研究院 Rotating turbine flow and cooling test device and method
CN107014618A (en) * 2017-03-29 2017-08-04 浙江大学 A kind of combustion chamber and turbine coupling mechanism experiment research device
CN207248535U (en) * 2017-08-30 2018-04-17 华能国际电力股份有限公司 Gas turbine blade end wall heat transfer test system
CN109139122A (en) * 2018-11-07 2019-01-04 哈尔滨电气股份有限公司 A kind of inner cooling system of 2 grades of turbine rotors of gas turbine
CN109812299A (en) * 2019-01-17 2019-05-28 杭州汽轮动力集团有限公司 A kind of gas turbine turbine rotor cooling means and cooling gas system
CN110069848A (en) * 2019-04-18 2019-07-30 西安交通大学 A kind of turbine blade is pneumatic-dehumidifying-cooling test modeling method
CN110132556A (en) * 2019-04-30 2019-08-16 中国航发湖南动力机械研究所 Modularization turbine test part and its test method
CN110261433A (en) * 2019-07-05 2019-09-20 西安交通大学 A kind of removal model experimental device of aviation gas turbine movable vane internal heat transfer
CN110726540A (en) * 2019-10-11 2020-01-24 中国航发沈阳发动机研究所 Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar
CN110700901A (en) * 2019-11-19 2020-01-17 中国特种设备检测研究院 Experimental device for be used for impeller machinery fault simulation and monitoring
CN110821883A (en) * 2019-12-04 2020-02-21 哈尔滨电气股份有限公司 Modularized compressor rotor applied to heavy gas turbine
CN111062124A (en) * 2019-12-05 2020-04-24 西安交通大学 Similar modeling method for supercritical carbon dioxide compressor test
CN111561356A (en) * 2020-05-20 2020-08-21 哈电发电设备国家工程研究中心有限公司 Be applied to heavy gas turbine's modularization turbine rotor
CN111735844A (en) * 2020-07-14 2020-10-02 西安交通大学 Experimental system and method for cooling test of front edge of turbine blade under rotation condition

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
张全付: ""西门子V94.3A型燃气轮机燃烧室及透平冷却技术"", 《科技创新与应用》, no. 1, 15 February 2015 (2015-02-15), pages 34 - 35 *
张广源: ""冷却空气系统对燃气轮机热力性能的影响"", 《中国优秀博硕士学位论文全文数据库(硕士) 工程科技Ⅱ辑》, no. 03, 15 March 2015 (2015-03-15), pages 039 - 153 *
张成利 等: ""燃气轮机二次空气系统的设计要求与布置特点分析"", 《燃气轮机技术》, vol. 23, no. 2, 27 August 2010 (2010-08-27), pages 39 - 42 *

Similar Documents

Publication Publication Date Title
CN110717219B (en) Method and device for acquiring inlet flow of air compressor in complete machine state of aero-engine
Ayder et al. Experimental and theoretical analysis of the flow in a centrifugal compressor volute
CN112444398A (en) Gas turbine rotor cold air conveying test piece and test parameter design method
CN112594064B (en) S2 flow field diagnosis method based on interstage measurement parameters of axial flow compressor
US6027305A (en) Method and apparatus for reducing high-cycle fatigue and suppressing noise in rotating machinery
Schuler et al. Experimental investigation of an aspirated fan stage
CN112287580A (en) Axial flow compressor surge boundary calculation method based on full three-dimensional numerical simulation
Li et al. Numerical and experimental research on different inlet configurations of high speed centrifugal compressor
Wilson An experimental determination of losses in a three-port wave rotor
CN113029573A (en) Low-Reynolds-number plane cascade high-altitude flow simulation device
Zhang et al. Gas-liquid two-phase flow in the axial clearance of liquid-ring pumps
CN112432793A (en) Gas turbine wheel disc air extraction test piece and modeling test parameter design method
CN106017908A (en) Rotating turbine flow and cooling test device and method
Hura et al. Reynolds number effects in a low pressure turbine
Li et al. Effect of rotor-stator axial gap on the tip seal leakage flow of a steam turbine
Pazur et al. The influence of inlet swirl distortions on the performance of a jet propulsion two-stage axial compressor
WOOD et al. NASA low-speed centrifugal compressor for fundamental research
Suder et al. Results of an advanced fan stage operating over a wide range of speed and bypass ratio: Part I—Fan stage design and experimental results
CN113202928A (en) Low-leakage wing-containing sealing structure
Grimshaw et al. Bleed-induced distortion in axial compressors
CN112325952A (en) Air flow measuring device flowing through rotary hole
Colantuoni et al. Aerodesign and performance analysis of a radial transonic impeller for a 9: 1 pressure ratio compressor
Fujisawa et al. Transient analysis of rotating stall development in a centrifugal compressor with vaned diffuser
Xi et al. Experimental and numerical investigations on flow losses of a U-Bend and return channel system for centrifugal compressor
CN113029577B (en) Expansion section for planar cascade flow simulation device

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
RJ01 Rejection of invention patent application after publication

Application publication date: 20210302

RJ01 Rejection of invention patent application after publication