CN110728052A - Method for determining boundary conditions of rotating disc cavity similarity test - Google Patents

Method for determining boundary conditions of rotating disc cavity similarity test Download PDF

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CN110728052A
CN110728052A CN201910964742.9A CN201910964742A CN110728052A CN 110728052 A CN110728052 A CN 110728052A CN 201910964742 A CN201910964742 A CN 201910964742A CN 110728052 A CN110728052 A CN 110728052A
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test
determining
inlet
pressure
condition
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CN110728052B (en
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李宗超
田申
吴小军
许亚楠
邱天
邓长春
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AECC Shenyang Engine Research Institute
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    • 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
    • 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

Abstract

The application belongs to the technical field of aero-engine tests, and particularly relates to a method for determining boundary conditions of a similar test of a rotating disc cavity, which comprises the steps of obtaining inlet temperature, inlet pressure, outlet pressure and physical rotating speed of a turbine disc cavity tested under the condition of the complete machine of an engine; setting an inlet temperature for performing a part test; determining the dynamic viscosity coefficients of the whole machine test and the part test through a Satherland formula; determining the inlet pressure of the part test; determining an outlet pressure for the part test; determining the rotation speed of the part test; and carrying out the component test according to the inlet temperature, the inlet pressure, the outlet pressure and the rotating speed of the component test. The method and the device have the advantages that the compressible and strong dissipation characteristics of the high-speed rotating disc cavity can be considered, and the boundary conditions of the part test can be directly converted according to the test data of the complete machine test of the engine; and only one degree of freedom exists, so that the similarity and the test reliability are ensured.

Description

Method for determining boundary conditions of rotating disc cavity similarity test
Technical Field
The application belongs to the technical field of aero-engine tests, and particularly relates to a method for determining boundary conditions of a rotary disc cavity similarity test.
Background
The gradual increase of the temperature in front of the turbine of the aircraft engine not only enables the performance of the engine to be continuously improved, but also enables the working environment of each stage of disk of the engine, particularly the turbine disk to be severe, and the analysis of the flowing heat exchange rule of the disk is of great importance to the heat transfer design work of the turbine disk. However, the test under the real environment of the whole machine is often limited by many practical conditions, for example, in the measurement of parameters such as flow, pressure, temperature and the like, the arrangement position and the number of the test points are limited by the practical situation of the engine, and are not too many, so that the detailed test work is required to be performed on a component test.
During the part test verification process, the real parameter level of the engine is required to be reduced, and the multi-working-condition test is carried out at a lower cost. This is necessary to determine the boundary conditions of the component test states and the parameters such as the physical rotational speed according to similar criteria based on known engine boundary conditions before the next component test can be performed.
In the existing component test, the characteristics of compressibility and strong dissipation of a high-speed rotating disk cavity are not considered; the boundary conditions of the component test cannot be directly converted according to the engine test data, more degrees of freedom exist, and complete similarity cannot be achieved.
Disclosure of Invention
In order to solve at least one of the technical problems, the application provides a method for determining the boundary conditions of the similarity test of the rotating disk cavity, which can consider the compressible and strong dissipation characteristics of the high-speed rotating disk cavity; and the boundary conditions of the component test can be directly converted according to the engine test data, only one degree of freedom exists, and after the specific numerical value of the degree of freedom is given, other boundary conditions can be calculated according to the application.
The method for determining the boundary conditions of the rotating disc cavity similarity test mainly comprises the following steps:
acquiring inlet temperature, inlet pressure, outlet pressure and physical rotating speed of a turbine disc cavity tested under the condition of the whole engine of the engine;
setting an inlet temperature for performing a part test;
determining the dynamic viscosity coefficients of the whole machine test and the part test through a Satherland formula;
determining the inlet pressure of the part test;
determining an outlet pressure for the part test;
determining the rotation speed of the part test;
and carrying out the component test according to the inlet temperature, the inlet pressure, the outlet pressure and the rotating speed of the component test.
Preferably, for a rotating disk cavity having multiple inlets, after the inlet temperature for the component test is given, the method further comprises determining each inlet temperature for the component test based on a ratio of the multiple inlet temperatures at the conditions of the complete machine.
Preferably, for a rotating disk chamber having a plurality of inlets, after determining the inlet pressure for the part test, further comprising determining each inlet pressure for the part test based on a ratio of the plurality of inlet pressures at the overall conditions.
Preferably, for a rotating disk chamber having a plurality of outlets, after determining the outlet pressure of the part test, further comprising determining each outlet pressure of the part test according to a ratio of the plurality of outlet pressures under the overall conditions.
Preferably, the inlet pressure P of the test of the determining means is1The method comprises the following steps:
P1`＝P1*μ1`/μ1*sqrt(T1`/T1)
wherein, P1Is the inlet pressure of the turbine disk cavity, mu, tested under the condition of the complete machine1To be integratedDynamic viscosity coefficient of mechanical test, T1Is the inlet temperature mu of the turbine disk cavity tested under the condition of the complete machine1"dynamic viscosity coefficient of part test, T1"is the inlet temperature for a given part test.
Preferably, the outlet pressure P' of the test of the determining meansout1The method comprises the following steps:
P`out1＝P`1*Pout1/P1
wherein, P' is1Inlet pressure, P, for testing of componentsout1Is the outlet pressure, P, of the turbine disk cavity tested under the condition of the complete machine1The inlet pressure of the turbine disc cavity tested under the condition of the complete machine.
Preferably, the speed of rotation N' for the test of the determining means comprises:
N`＝N*sqrt(T`/T)
wherein N is the rotating speed of the turbine disc cavity tested under the condition of the complete machine, T' is the inlet temperature of the given component test, and T is the inlet temperature of the turbine disc cavity tested under the condition of the complete machine.
The application has the advantages that:
a) the compressible and high-dissipation characteristics of the high-speed rotating disk cavity can be considered;
b) considering that the engine can only measure temperature, pressure and the like, but can not measure references such as flow, speed, density and the like, the method can directly convert the test data of the engine to obtain boundary conditions of a component test;
c) only one degree of freedom exists, and after a specific numerical value of the degree of freedom is given, other boundary conditions can be calculated, so that the similarity and the test reliability are guaranteed.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the method of determining the boundary conditions of a spinning disk chamber-like test of the present application.
FIG. 2 is a flow diagram of a two-in three-out turntable cavity of a preferred embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a method for determining boundary conditions of a rotating disk cavity similarity test, as shown in fig. 1, which mainly comprises the following steps:
step S1, acquiring the inlet temperature, inlet pressure, outlet pressure and physical rotation speed of the turbine disc cavity tested under the condition of the complete engine;
step S2, setting an inlet temperature for carrying out a component test;
step S3, determining the dynamic viscosity coefficients of the whole machine test and the part test through a Satherland formula;
step S4, determining the inlet pressure of the component test;
step S5, determining the outlet pressure of the component test;
step S6, determining the rotation speed of the component test;
and step S7, developing the component test according to the inlet temperature, the inlet pressure, the outlet pressure and the rotating speed of the component test.
In step S1, assuming that the rotating disk cavity is single-in and single-out and the geometric model is unchanged, the inlet temperature T of the turbine disk cavity tested under the condition of the complete engine is known1Inlet pressure P1Outlet pressure Pout1Physical speed N, step S2 specifies the inlet temperature T at a similar condition for the part test1"one degree of freedom only, which can be given by the user in terms of tester capabilities, without being bound by a theoretical formula) Step S3-step S4 calculate the inlet pressure P of the part test1"on this basis, step S5 gives the outlet pressure P' out of the part test1On the basis of step S2, the physical rotation speed N' of the component test can be calculated, and thus all the inlet pressure, temperature, outlet pressure, physical rotation speed and boundary conditions of the component test are obtained, and all the boundary conditions required for the component test are satisfied.
In step S3, the dynamic viscosity coefficient is calculated using the satherland formula, for example, the dynamic viscosity coefficient u of the part test is obtained from the inlet temperature T and the satherland formula.
Figure BDA0002230112050000041
Wherein for air, mu0＝17.61×10-6(Pa·S)，Ts＝124(K)。
In some alternative embodiments, for a rotating disk chamber having multiple inlets, after a given inlet temperature at which a component test is performed, further comprising determining each inlet temperature for the component test based on a ratio of the multiple inlet temperatures at overall conditions.
In some alternative embodiments, for a rotating disk chamber having a plurality of inlets, after determining the inlet pressure for the part test, further comprising determining each inlet pressure for the part test based on a ratio of the plurality of inlet pressures at the overall condition.
In some alternative embodiments, for a rotating disk chamber having a plurality of outlets, after determining the outlet pressure for the part test, further comprising determining each outlet pressure for the part test based on a ratio of the plurality of outlet pressures at the overall condition.
In some alternative embodiments, the determining component tests the inlet pressure P1The method comprises the following steps:
P1`＝P1*μ1`/μ1*sqrt(T1`/T1)
wherein, P1Inlet pressure of turbine disk cavity tested under complete machine conditionForce, mu1Dynamic viscosity coefficient, T, for the complete machine test1Is the inlet temperature mu of the turbine disk cavity tested under the condition of the complete machine1"dynamic viscosity coefficient of part test, T1"is the inlet temperature for a given part test.
In some alternative embodiments, the determination of the outlet pressure P' of the part testout1The method comprises the following steps:
P`out1＝P`1*Pout1/P1
wherein, P' is1Inlet pressure, P, for testing of componentsout1Is the outlet pressure, P, of the turbine disk cavity tested under the condition of the complete machine1The inlet pressure of the turbine disc cavity tested under the condition of the complete machine.
In some alternative embodiments, said determining the rotational speed N' of the component test comprises:
N`＝N*sqrt(T`/T)
wherein N is the rotating speed of the turbine disc cavity tested under the condition of the complete machine, T' is the inlet temperature of the given component test, and T is the inlet temperature of the turbine disc cavity tested under the condition of the complete machine.
It should be noted that the above formula of the present application has considered compressibility and dissipation of the high velocity gas flow. By adopting the formula, the complete machine test and the part test can be ensured that the flow heat transfer rule of the rotating disc cavity is completely similar.
FIG. 2 shows a schematic diagram of a two-in-three-out rotating disk cavity, where a first set of intake air inlet parameters includes, for known engine conditions: p1、T1(ii) a Physical rotation speed N; geometric dimension d (diameter); solid heat conductivity coefficient lambdaS(ii) a The second set of intake air inlet parameters includes: p2、T2(ii) a Outlet 1 boundary condition is Pout1(ii) a Outlet 2 boundary condition is Pout2(ii) a Outlet 3 boundary condition is Pout3。
By means of the boundary conditions, and under the condition that the inlet temperature of the part test is given, the boundary conditions and the physical rotating speed of all other inlets and outlets of the part test can be determined.
The method comprises the following specific steps:
1) for first useHousehold self-determination of inlet air temperature T of part test inlet 11`；
2) According to the inlet temperature T of the whole machine1The inlet dynamic viscosity coefficient mu is calculated by the Satherland formula1According to the inlet temperature T of the component1Calculating to obtain the component inlet dynamic viscosity coefficient mu' through the Satherland formula1；
3) The part test inlet 1 pressure is derived according to the following formula, namely:
P1`＝P1*μ1`/μ1*sqrt(T1`/T1)；
4) the pressure at the test outlet 1 of the part, P' out, is derived according to the following equation1＝P`1*Pout1/P1；
5) The part test inlet 2 pressure, P' is derived according to the following equation2＝P`1*P2/P1；
6) The part test inlet 2 temperature, T' is derived from the following equation2＝T`1*T2/T1；
7) The pressure at the test outlet 2 of the part, P' out, is derived according to the following equation2＝P`1*Pout2/P1；
8) The part test outlet 3 pressure, P' out, is derived from the following equation3＝P`1*Pout3/P1；
9) The test speed of the component, i.e., N ═ N × sqrt (T'/T), is obtained according to the following formula.
Thus, all inlet pressures, temperatures, outlet pressures, and boundary conditions of the component test are closed, and all boundary conditions required for conducting the component test are met.
The application has the advantages that:
a) the compressible and high-dissipation characteristics of the high-speed rotating disk cavity can be considered;
b) considering that the engine can only measure temperature, pressure and the like, but can not measure references such as flow, speed, density and the like, the method can directly convert the test data of the engine to obtain boundary conditions of a component test;
c) only one degree of freedom exists, and after a specific numerical value of the degree of freedom is given, other boundary conditions can be calculated, so that the similarity and the test reliability are guaranteed.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (7)

1. A method of determining boundary conditions for a rotating disk chamber similarity test, comprising:
acquiring inlet temperature, inlet pressure, outlet pressure and physical rotating speed of a turbine disc cavity tested under the condition of the whole engine of the engine;
setting the inlet temperature of a turbine disc cavity for carrying out part test;
determining the dynamic viscosity coefficients of the whole machine test and the part test through a Satherland formula;
determining the inlet pressure of the part test;
determining an outlet pressure for the part test;
determining the rotation speed of the part test;
and carrying out the component test according to the inlet temperature, the inlet pressure, the outlet pressure and the rotating speed of the component test.
2. The method of determining boundary conditions for a rotating disk chamber similarity test as claimed in claim 1 wherein for a rotating disk chamber having a plurality of inlets, after a given inlet temperature at which a part test is conducted, further comprising determining each inlet temperature for the part test based on a ratio of the plurality of inlet temperatures at the conditions of the complete machine.
3. The method of determining a rotating disk chamber similarity test boundary condition as claimed in claim 1 wherein, for a rotating disk chamber having a plurality of inlets, after determining the inlet pressure for the part test, further comprising determining each inlet pressure for the part test based on a ratio of the plurality of inlet pressures for the overall condition.
4. The method of determining a rotating disk chamber similarity test boundary condition as claimed in claim 1 wherein, for a rotating disk chamber having a plurality of outlets, after determining the outlet pressure for the part test, further comprising determining each outlet pressure for the part test based on a ratio of the plurality of outlet pressures for the overall condition.
5. A method of determining the boundary conditions of a rotating disc chamber similarity test as claimed in claim 1 wherein the inlet pressure P of the component test is determined1The method comprises the following steps:
P1`＝P1*μ1`/μ1*sqrt(T1`/T1)
wherein, P1Is the inlet pressure of the turbine disk cavity, mu, tested under the condition of the complete machine1Dynamic viscosity coefficient, T, for the complete machine test1Is the inlet temperature mu of the turbine disk cavity tested under the condition of the complete machine1"dynamic viscosity coefficient of part test, T1"is the inlet temperature for a given part test.
6. The method of determining the boundary conditions of a rotating disk chamber similarity test as claimed in claim 1, wherein said determining the exit pressure P "of the part testout1The method comprises the following steps:
P`out1＝P`1*Pout1/P1
wherein, P' is1Inlet pressure, P, for testing of componentsout1Is the outlet pressure, P, of the turbine disk cavity tested under the condition of the complete machine1The inlet pressure of the turbine disc cavity tested under the condition of the complete machine.
7. A method of determining the boundary conditions of a rotary disk chamber similarity test as defined in claim 1, wherein said determining the rotational speed N' of the member test comprises:
N`＝N*sqrt(T`/T)
wherein N is the rotating speed of the turbine disc cavity tested under the condition of the complete machine, T' is the inlet temperature of the given component test, and T is the inlet temperature of the turbine disc cavity tested under the condition of the complete machine.
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