CN110726540B - Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar - Google Patents
Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar Download PDFInfo
- Publication number
- CN110726540B CN110726540B CN201910963921.0A CN201910963921A CN110726540B CN 110726540 B CN110726540 B CN 110726540B CN 201910963921 A CN201910963921 A CN 201910963921A CN 110726540 B CN110726540 B CN 110726540B
- Authority
- CN
- China
- Prior art keywords
- inlet
- test
- heat transfer
- outlet
- whole machine
- 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.)
- Active
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
- G01M13/00—Testing of machine parts
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The application belongs to the technical field of aero-engine tests, and particularly relates to a method for controlling flow heat transfer phenomena of a multi-input multi-output rotary disc cavity to be completely similar, wherein the method comprises the steps of adjusting parameters of a rotary disc cavity test piece to enable the air inlet Reynolds number, the rotary Reynolds number, the air inlet Mach number, the heat insulation index and the Prandt number of the test piece and the ratio of the solid heat conductivity coefficient to the air flow inlet heat conductivity coefficient to be the same as that of a complete machine test; for the rotating disk cavity test piece with more than one inlet and one outlet, two dimensionless numbers of the inlet dimensionless speed ratio and the inlet dimensionless temperature ratio of each inlet of the exceeding part relative to the first inlet are the same as those of the whole machine test, and the dimensionless pressure ratio of the outlet of each outlet of the exceeding part relative to the first inlet is the same as that of the whole machine test. The method and the device ensure that the flow heat transfer phenomena of the two multi-inlet and multi-outlet rotating disc cavities are completely similar by ensuring that the dimensionless numbers of the whole machine test and the component test are the same, and ensure the reliability of the test.
Description
Technical Field
The application belongs to the technical field of aero-engine tests, and particularly relates to a method for controlling flow heat transfer phenomena of a multi-inlet multi-outlet rotary disc cavity to be completely similar.
Background
An aircraft engine is a typical high-speed rotating machine. Turbine disks are an important component of aircraft engines. The chamber formed by the turbine disk and the stator part at the periphery of the turbine disk is called a rotating disk chamber. The problem of flow heat transfer in a rotating disc chamber is a specialized field of research in academia.
In order to reduce the difficulty of testing an aircraft engine rotating disc chamber, it is common to perform tests by reducing the associated pressure temperature level in a similar manner. While the parameters are reduced, the situation that the part test is completely similar to the real test of the whole machine needs to be ensured, so that the conclusion of the part test can support the work of the whole machine.
The traditional experiment mainly comprises the steps of scaling a part of related parameters in an equal ratio, and has the defect that the considered parameters are few, and mainly means that the traditional similar criterion parameters have the characteristics of not considering compressibility, not considering a dissipation term of air flow and not considering the condition of multiple input and multiple output.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a method for controlling flow heat transfer phenomena of multiple-input multiple-output rotating disc cavities to be completely similar, based on dimensionless parameters derived theoretically, various factors can be considered comprehensively, and by ensuring that the dimensionless numbers of a complete machine test and a component test are equal, the flow heat transfer phenomena of two multiple-input multiple-output rotating disc cavities can be ensured to be completely similar, that is, pressure, speed, fluid temperature, solid temperature and the like are completely similar.
The method for controlling the flow heat transfer phenomena of the multi-inlet multi-outlet rotating disc cavity is completely similar, and mainly comprises the following steps:
adjusting parameters of a test piece of the rotary disk cavity to enable six dimensionless numbers of an air inlet Reynolds number, a rotary Reynolds number, an air inlet Mach number, a heat insulation index, a Prandtl number and a ratio of a solid heat conductivity coefficient to an air flow inlet heat conductivity coefficient of the test piece to be the same as that of a complete machine test;
for the rotating disk cavity test piece with more than one inlet and one outlet, for each inlet of the exceeding part, adjusting the parameters of the rotating disk cavity test piece at the corresponding inlet to ensure that the two dimensionless numbers of the inlet dimensionless speed ratio and the inlet dimensionless temperature ratio of the rotating disk cavity test piece relative to the first inlet are the same as those of the whole machine test, and for each outlet of the exceeding part, adjusting the parameters of the rotating disk cavity test piece at the corresponding outlet to ensure that the outlet dimensionless pressure ratio of the rotating disk cavity test piece relative to the first inlet is the same as that of the whole machine test.
Preferably, the inlet flow rate of the component test is adjusted to ensure that the inlet Reynolds numbers of the component test and the complete machine test are equal.
Preferably, the rotating Reynolds numbers of the component test and the complete machine test are equal by adjusting the rotating speed of the component test.
Preferably, the inlet speed or the temperature of the part test is adjusted to ensure that the inlet Mach number of the part test is equal to that of the whole machine test.
Preferably, the thermal insulation indexes of the component test and the complete machine test are ensured to be equal by adjusting the gas constant of the component test.
Preferably, the prandtl number of the component test and the whole test is ensured to be equal by adjusting the physical property parameters of the component test.
Preferably, the ratio of the solid heat conductivity coefficient to the air flow inlet heat conductivity coefficient of the part test and the whole machine test is equal by adjusting the material of the solid disc of the part test.
Preferably, the air inlet speeds of other inlets of the component test are adjusted to ensure that the inlet non-dimensional speed ratio of the inlet at the position of the component test and the inlet at the first position of the complete machine test is equal.
Preferably, the inlet air temperature of other inlets of the component test is adjusted to ensure that the inlet air dimensionless temperature ratio of the inlet at the position of the component test and the inlet at the first position of the complete machine test is equal.
Preferably, the pressure of other outlets of the part test is adjusted to ensure that the inlet non-dimensional pressure ratio of the outlet at the part test position and the inlet at the first position of the whole machine test position is equal.
The method for controlling the flow heat transfer phenomena of the multi-input multi-output rotating disc cavity is completely similar, and overcomes the defects that the compressibility, the dissipation item of air flow and the multi-input multi-output condition are not considered in the traditional method. The flow heat transfer phenomena of the two multi-inlet and multi-outlet rotating disc cavities are completely similar by ensuring that the dimensionless numbers of the whole machine test and the part test are equal, so that the test precision is improved, and the test reliability is ensured.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of the present application for a method of controlling flow heat transfer in multiple-out rotating disk chambers that is completely similar.
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 present application provides a method for controlling the flow heat transfer phenomena of a multi-inlet multi-outlet rotating disk cavity completely similar, as shown in fig. 1, mainly comprising:
and step S1, adjusting parameters of the test piece of the rotating disc cavity, and enabling six dimensionless numbers of the air inlet Reynolds number, the rotating Reynolds number, the air inlet Mach number, the adiabatic index, the Prandtl number and the ratio of the solid heat conductivity coefficient to the air inlet heat conductivity coefficient of the test piece to be the same as that of the whole machine test.
And step S2, for the rotating disk cavity test piece with more than one inlet and one outlet, for each inlet of the more than part, adjusting the parameters of the rotating disk cavity test piece at the corresponding inlet, so that the two dimensionless numbers of the inlet dimensionless speed ratio and the inlet dimensionless temperature ratio of the rotating disk cavity test piece relative to the first inlet are the same as those of the whole machine test, and for each outlet of the more than part, adjusting the parameters of the rotating disk cavity test piece at the corresponding outlet, so that the outlet dimensionless pressure ratio of the rotating disk cavity test piece relative to the first inlet is the same as that of the whole machine test.
The definition of the partial dimensionless number is as follows: re ═ ρ × u × d/μ; rew＝ρ*w*d^2/μ；Ma＝u/sqrt(k*Rg*t)；k＝cp/cv；Pr＝μ*cp/λ。
Wherein ρ is density; u is the velocity; d is the diameter of the disc; w is the rotational speed of the disc; mu is dynamic viscosity coefficient; t is the temperature; c. CpIs the specific heat at constant pressure; c. CvThe specific heat capacity is constant volume, and the lambda is the gas heat conductivity coefficient.
Re is inlet Reynolds number, RewIs the Reynolds number of rotation, Ma is the intake Mach number, k is the adiabatic index, Pr is the Plantt number, and the ratio of the solid thermal conductivity to the gas stream inlet thermal conductivity
Step S1 is for single-in single-out rotating disk chamber test piece, for convenience of description, the single-in single-out is referred to as a first group of in-out and out-put, or a first inlet and a first outlet, and step S2 is for multiple-in multiple-out rotating disk chamber test piece, the more than partial inlet and outlet are referred to as a second inlet and a second outlet … ….
In step S2, for each inlet of the excess portion, e.g., the second inlet, the rotating disk chamber test piece parameters at the corresponding inlet are adjusted to provide a non-dimensional air-intake velocity ratio with respect to the first inlet
And the dimensionless temperature ratio of the inlet air
The two dimensionless numbers are the same as those of the whole machine test, and similarly, for each outlet of the excess part, for example the second outlet, the parameters of the test piece in the rotary disk cavity at the corresponding outlet are adjusted to make the dimensionless pressure ratio of the outlet air of the test piece relative to the first inlet
As with the complete machine test, where the relevant reference to the first inlet is denoted with a subscript of 0 and the relevant parameter to the second inlet or the second outlet is denoted with a subscript of 2.
It will be understood by those skilled in the art that, according to the description of step S2, if one more entry is added, the first two dimensionless numbers in step S2 need to be added; if one more exit is added, then the last dimensionless number in step S2 needs to be added. That is, adding one inlet will add two dimensionless numbers; adding an outlet adds a dimensionless number.
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: u. of0，ρ0，t0，μ0，λ0，cp0(ii) a Physical rotation speed w; a geometric dimension d; a gas constant Rg; solid heat conductivity coefficient lambdaS(ii) a The second set of intake air inlet parameters includes: u. of2，t2(ii) a Outlet 1 does not require boundary conditions; the outlet 2 boundary conditions include: p is a radical of2(ii) a Outlet 3 boundary conditions include p3。
The specific values of the dimensionless numbers described in the above section are obtained by the above boundary conditions, and the total number includes 10 dimensionless numbers. By ensuring that the dimensionless number values of the test states of the parts are completely equal to the 10 numbers of the states of the whole machine, the two tests can be ensured to be completely similar, namely the pressure, the speed, the fluid temperature, the solid temperature and the like are completely similar.
The method comprises the following specific steps:
1) the inlet flow of the component test is adjusted to ensure that the inlet Reynolds numbers of the component test and the whole machine test are equal;
2) the rotating Reynolds numbers of the component test and the whole machine test are equal by adjusting the rotating speed of the component test;
3) the inlet speed or temperature of the component test is adjusted to ensure that the inlet Mach number of the component test is equal to that of the whole machine test;
4) the gas constant of the part test is adjusted to ensure that the adiabatic indexes of the part test and the whole machine test are equal, and if the adiabatic indexes are the same as air, the adjustment is not needed;
5) the prandtl number of the part test and the whole machine test is equal by adjusting the physical property parameters of the part test;
6) the ratio of the solid heat conductivity coefficient to the heat conductivity coefficient of the air inlet of the part test and the whole machine test is equal by adjusting the material of the solid disc of the part test;
7) the air inlet speed of the inlet 2 of the component test is adjusted to ensure that the air inlet dimensionless speed ratio of the inlet at the other part of the component test and the whole machine test is equal;
8) the inlet air temperature of the inlet 2 of the component test is adjusted to ensure that the inlet air dimensionless temperature ratio of the inlet at the other part of the component test and the whole machine test is equal;
9) the pressure of the outlet 2 of the part test is adjusted to ensure that the outlet dimensionless pressure ratio of the outlet at the other part of the part test and the whole machine test is equal.
10) The pressure of the outlet 3 of the part test is adjusted to ensure that the outlet dimensionless pressure ratio of the outlet at the other part of the part test and the whole machine test is equal.
A specific example is given below, wherein the known overall test parameters (reference example) are:
the inlet speed is 100m/s, and the inlet temperature is 673K;
ideal gas physical properties: specific heat 1068J/(kg.K), dynamic viscosity 3.3e-5 kg/(m.s), thermal conductivity 0.0521W/(m.K);
the rotating speed is 10000 r/min;
outlet static pressure 400000 Pa;
rotating wall surface rolling constant temperature boundary 773K, Static wall surface Static thermal insulation.
When a part similarity test is carried out, in order to ensure that 6 dimensionless numbers of the similarity verification are not changed, the relevant parameters of the given example are as follows:
the inlet velocity is 200m/s (preset to be 2 times of the numerical value of the reference calculation), the ideal aerodynamic viscosity is 6.6e-5 kg/(m.s) (preset to be 2 times of the numerical value of the reference calculation), and other numerical values are gradually deduced on the premise of ensuring that dimensionless numbers are equal, and the method respectively comprises the following steps:
1) the inlet temperature is 2692K (ensuring that Ma is pushed out constantly);
2) ideal gas physical properties: specific heat 1068J/(kg.K) (ensuring that K is constantly pushed out), and thermal conductivity 0.1042W/(m.K) (ensuring that Pr is constantly pushed out);
3) the rotating speed is 20000r/min (ensuring constant Rew push-out);
4) outlet static pressure 1600000Pa (ensuring inlet Re is constant, the inlet density rho is required to be kept constant, further rho distribution is kept constant, outlet rho is constant, and according to P ═ rho RgT can push out the outlet pressure);
5) the Rotating wall temperature setting boundary 3092K and the Static wall Static heat insulation.
According to the method, under the condition that boundary parameters are different, the distribution and dimensionless numbers of results are completely the same, namely the descriptions are completely similar, the CFD verification is passed, the results show that the swirl ratio and the Nurseel number are in accordance with expectations, the flowing heat transfer phenomena of two multi-inlet multi-outlet rotating disc cavities of a complete machine test and a component similarity test are completely similar, the test precision is improved, and the test reliability is 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 (10)
1. A method for controlling flow heat transfer phenomena of a multi-inlet multi-outlet rotating disc cavity to be completely similar is characterized by comprising the following steps:
adjusting parameters of a test piece of the rotary disk cavity to enable six dimensionless numbers of an air inlet Reynolds number, a rotary Reynolds number, an air inlet Mach number, a heat insulation index, a Prandtl number and a ratio of a solid heat conductivity coefficient to an air flow inlet heat conductivity coefficient of the test piece to be the same as that of a complete machine test;
for the rotating disk cavity test piece with more than one inlet and one outlet, for each inlet of the exceeding part, adjusting the parameters of the rotating disk cavity test piece at the corresponding inlet to ensure that the two dimensionless numbers of the inlet dimensionless speed ratio and the inlet dimensionless temperature ratio of the rotating disk cavity test piece relative to the first inlet are the same as those of the whole machine test, and for each outlet of the exceeding part, adjusting the parameters of the rotating disk cavity test piece at the corresponding outlet to ensure that the inlet dimensionless pressure ratio of the rotating disk cavity test piece relative to the first inlet is the same as that of the whole machine test.
2. The method for controlling the flow heat transfer phenomena of the multiple-input multiple-output rotating disk cavity to be completely similar as claimed in claim 1, wherein the intake Reynolds numbers of the component test and the complete machine test are ensured to be equal by adjusting the flow rate of the inlet airflow of the component test.
3. The method for controlling the flow heat transfer phenomena of the multiple-input multiple-output rotating disc cavity to be completely similar as claimed in claim 1, wherein the rotating Reynolds numbers of the component test and the whole machine test are ensured to be equal by adjusting the rotating speed of the component test.
4. The method for controlling the flow heat transfer phenomena of the multiple-input multiple-output rotating disc cavity as claimed in claim 1 is completely similar, characterized in that the inlet Mach numbers of the part test and the whole machine test are ensured to be equal by adjusting the speed or the temperature of the inlet airflow of the part test.
5. The method for controlling flow heat transfer phenomena of a multi-in multi-out rotating disc cavity as claimed in claim 1, wherein the adiabatic index of the part test and the whole machine test is ensured to be equal by adjusting the gas constant of the part test.
6. The method for controlling the flow heat transfer phenomena of the multiple-input multiple-output rotating disc cavity to be completely similar as claimed in claim 1, wherein the Plantt number of the part test and the whole machine test is ensured to be equal by adjusting physical parameters of the part test.
7. The method for controlling multiple-input multiple-output rotating disk cavity flow heat transfer phenomena completely similar as claim 1, wherein the ratio of solid heat conductivity coefficient to airflow inlet heat conductivity coefficient is equal between part test and whole machine test by adjusting the material of the solid disk of the test piece.
8. The method for controlling flow heat transfer phenomena in a multi-in multi-out rotating disc cavity of claim 1, wherein the inlet air non-dimensional speed ratio of the inlet to the first inlet at the position of the part test and the whole machine test is ensured to be equal by adjusting the inlet air speed of other inlets of the test piece.
9. The method for controlling flow heat transfer phenomena in a multi-in multi-out rotating disc cavity of claim 1, wherein the inlet air temperature ratio of the inlet to the first inlet at the part test and the whole machine test is ensured to be equal by adjusting the inlet air temperature of other inlets of the test piece.
10. The method for controlling flow heat transfer phenomena in a multiple-input multiple-output rotating disk cavity of claim 1 is completely similar, wherein the pressure of other outlets of the test piece is adjusted to ensure that the inlet non-dimensional pressure ratio of the outlet and the first inlet at the part test position is equal to that of the whole machine test position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963921.0A CN110726540B (en) | 2019-10-11 | 2019-10-11 | Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910963921.0A CN110726540B (en) | 2019-10-11 | 2019-10-11 | Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110726540A CN110726540A (en) | 2020-01-24 |
| CN110726540B true CN110726540B (en) | 2021-06-08 |
Family
ID=69221050
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910963921.0A Active CN110726540B (en) | 2019-10-11 | 2019-10-11 | Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110726540B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112444398A (en) * | 2020-11-23 | 2021-03-05 | 东方电气集团东方汽轮机有限公司 | Gas turbine rotor cold air conveying test piece and test parameter design method |
| CN112432793A (en) * | 2020-11-23 | 2021-03-02 | 东方电气集团东方汽轮机有限公司 | Gas turbine wheel disc air extraction test piece and modeling test parameter design method |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102565119A (en) * | 2010-12-14 | 2012-07-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for measuring cooling effect and thermal insulation effect of turbine blade with thermal barrier coating |
| CN105300695A (en) * | 2015-09-22 | 2016-02-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Turbine rotating disc cavity flow heat exchange formula correction coefficient determination method |
| CN107167322A (en) * | 2016-03-08 | 2017-09-15 | 贺利实公司 | The wireless engine monitoring system for controlling to network with aircraft for environmental emission |
| CN107238627A (en) * | 2017-05-31 | 2017-10-10 | 中国科学院上海应用物理研究所 | Conduction oil working medium forced circulation Comprehensive Experiment circuit system |
| CN108268713A (en) * | 2018-01-09 | 2018-07-10 | 上海交通大学 | The design method and prototype of prototype based on diesel combustion similarity theory |
| CN108536922A (en) * | 2018-03-20 | 2018-09-14 | 北京航空航天大学 | The internal and external flow field integration method for numerical simulation of aircraft and engine |
| CN109029907A (en) * | 2018-07-18 | 2018-12-18 | 大连理工大学 | A kind of parameter similar method of pneumatic thermal environmental test simulated conditions |
| US10288520B1 (en) * | 2017-02-24 | 2019-05-14 | Florida Turbine Technologies, Inc | Apparatus and process for testing an aero vehicle at high Mach number |
| CN109870298A (en) * | 2019-03-29 | 2019-06-11 | 西安工业大学 | A kind of evaluation method for simulating mini pile rigid connection structure antiskid performance |
-
2019
- 2019-10-11 CN CN201910963921.0A patent/CN110726540B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102565119A (en) * | 2010-12-14 | 2012-07-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for measuring cooling effect and thermal insulation effect of turbine blade with thermal barrier coating |
| CN105300695A (en) * | 2015-09-22 | 2016-02-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Turbine rotating disc cavity flow heat exchange formula correction coefficient determination method |
| CN107167322A (en) * | 2016-03-08 | 2017-09-15 | 贺利实公司 | The wireless engine monitoring system for controlling to network with aircraft for environmental emission |
| US10288520B1 (en) * | 2017-02-24 | 2019-05-14 | Florida Turbine Technologies, Inc | Apparatus and process for testing an aero vehicle at high Mach number |
| CN107238627A (en) * | 2017-05-31 | 2017-10-10 | 中国科学院上海应用物理研究所 | Conduction oil working medium forced circulation Comprehensive Experiment circuit system |
| CN108268713A (en) * | 2018-01-09 | 2018-07-10 | 上海交通大学 | The design method and prototype of prototype based on diesel combustion similarity theory |
| CN108536922A (en) * | 2018-03-20 | 2018-09-14 | 北京航空航天大学 | The internal and external flow field integration method for numerical simulation of aircraft and engine |
| CN109029907A (en) * | 2018-07-18 | 2018-12-18 | 大连理工大学 | A kind of parameter similar method of pneumatic thermal environmental test simulated conditions |
| CN109870298A (en) * | 2019-03-29 | 2019-06-11 | 西安工业大学 | A kind of evaluation method for simulating mini pile rigid connection structure antiskid performance |
Non-Patent Citations (1)
| Title |
|---|
| 旋转盘腔流动与换热试验准则;秦敏等;《燃气涡轮试验与研究》;20140430;第27卷(第2期);第34-36、53页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110726540A (en) | 2020-01-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110726540B (en) | Method for controlling flow heat transfer phenomena of multiple-inlet multiple-outlet rotating disc cavity to be completely similar | |
| Atkins | Investigation of a radial-inflow bleed as a potential for compressor clearance control | |
| Defoe et al. | Fan performance scaling with inlet distortions | |
| Graham | Fundamental mechanisms that influence the estimate of heat transfer to gas turbine blades | |
| Baghdadi | Modeling tip clearance effects in multistage axial compressors | |
| Gelain et al. | Conjugate heat transfer analysis of a surface air-cooled oil cooler (SACOC) installed in a turbofan by-pass duct. | |
| Fildes et al. | Analysis of boundary layer flow over a broad rotating cone in still fluid with non-stationary modes | |
| Shahrokhi et al. | Application of a modified dynamic compression system model to a low aspect ratio fan-effects of inlet distortion | |
| Jonsson et al. | Design of Chalmers new low-pressure compressor test facility for low-speed testing of cryo-engine applications | |
| Alqefl et al. | Aero-Thermal Aspects of Film Cooled Nozzle Guide Vane Endwall—Part 1: Aerodynamics | |
| Qi et al. | Influence of disc spacing distance on the aerodynamic performance and flow field of Tesla turbines | |
| Sebelev et al. | Aerodynamic analysis of the small-scaled centrifugal compressor for micro-turbojet engine applications | |
| Graber Jr et al. | Summary of recent investigations of inlet flow distortion effect on engine stability | |
| Heinlein et al. | Aerodynamic Behavior of a Coupled Boundary Layer Ingesting Inlet–Distortion Tolerant Fan | |
| Debuchy et al. | Investigation of the fluid flow in an isolated rotor-stator system with a peripheral opening | |
| Mutama et al. | The investigation of developing flow and heat transfer in a long converging duct | |
| Methel | An experimental comparison of diffuser designs in a centrifugal compressor | |
| Huntley et al. | Effect of Circumferential Total-Pressure Gradients Typical of Single-Inlet Duct Installations on Performance of an Axial-Flow Turbojet Engine | |
| Schwarz et al. | Considerations for gas stand measurement of turbocharger performance | |
| Joubert | Flowfield calculation in compressor operating with distorted inlet flow | |
| CN112906322B (en) | Method for calculating internal parameters of disk cavity of gas turbine engine | |
| Baghdadi | Modeling Tip Clearance Efects in Multi–Stage Axial Compressors | |
| Pitz et al. | Direct numerical simulation of radial convection in a cylindrical annulus with and without rotation | |
| Quanyong et al. | The Influences of Combined Distortions on Fan Performance | |
| Yu et al. | Experimental study on the blade tip clearance sensitive effect in compressors with different loading levels |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |