CN113221294B - Method for obtaining expansion ratio of high-low pressure turbine under engine complete machine condition - Google Patents
Method for obtaining expansion ratio of high-low pressure turbine under engine complete machine condition Download PDFInfo
- Publication number
- CN113221294B CN113221294B CN202110678694.4A CN202110678694A CN113221294B CN 113221294 B CN113221294 B CN 113221294B CN 202110678694 A CN202110678694 A CN 202110678694A CN 113221294 B CN113221294 B CN 113221294B
- Authority
- CN
- China
- Prior art keywords
- pressure
- outlet
- total pressure
- pressure turbine
- compressor
- 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
- 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
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application belongs to the technical field of aero-engine tests, and particularly relates to a method for obtaining a high-low pressure turbine expansion ratio under the condition of an engine complete machine. The method comprises the following steps: step S1, acquiring total pressure of an outlet of a compressor, total pressure recovery coefficient of a main combustion chamber and total pressure of an outlet of a high-pressure turbine; step S2, determining the high-pressure turbine expansion ratio; step S3, acquiring total pressure P of the outlet of the low-pressure turbine 5 (ii) a Step S4, the high pressure turbo expansion ratio is determined. The high-low pressure turbine expansion ratio under the complete machine condition is obtained based on the actual measurement test data of the complete machine, so that more accurate evaluation results of the high-low pressure turbine expansion ratio under the complete machine condition can be obtained, and the method has important significance for realizing more accurate evaluation of the complete machine performance and the performance of the turbine component under the complete machine condition.
Description
Technical Field
The application belongs to the technical field of aero-engine tests, and particularly relates to a method for obtaining a high-low pressure turbine expansion ratio under the condition of a complete engine.
Background
With the continuous and deep research on the performance of the whole aircraft engine, the accurate evaluation of the expansion ratio of the high-pressure turbine and the low-pressure turbine of the double-rotor turbofan engine under the whole condition gradually becomes one of the problems to be solved urgently, and the accurate evaluation directly influences the matching of the whole aircraft engine and the performance evaluation of parts.
At present, the total pressure of the outlet of a compressor and a casing support plate at the back of a turbine of a double-rotor turbofan engine can be measured under the condition of the whole machine, and the expansion ratio of a high-pressure turbine and a low-pressure turbine is obtained through a performance simulation model and a part test result.
The existing technical method is to combine the cross section pressure measurement results of partial runners of the whole machine, and adopt an engine overall performance simulation model to calculate and obtain the high-pressure turbine expansion ratio and the low-pressure turbine expansion ratio under the whole machine condition, because the difference between the part test condition and the whole machine environment is large, different working environment conditions can not be simulated generally, so that the part characteristics and the real performance of the part on the whole machine have large difference, and in addition, the evaluation of the whole machine and the turbine part performance under the whole machine condition and the determination of the whole machine performance matching optimization hardware resources can be influenced by the influence of the calculation precision of the overall performance simulation model, and the calculated high-pressure turbine expansion ratio and the calculated low-pressure turbine expansion ratio have large deviation with the actual result, so that the engineering application can not be well realized on the technical level.
Disclosure of Invention
In order to solve the above problems, the present application provides a method for obtaining a high-low pressure turbine expansion ratio under the condition of an engine complete machine, comprising:
s1, S1, obtaining total pressure P of the outlet of the compressor 3 Main combustion chamber total pressure recovery coefficient sigma 3-4 And total pressure P at the outlet of the high-pressure turbine 43 ；
Step S2, determining the high-pressure turbine expansion ratio pi TH ：π TH ＝P 3 *σ 3-4 /P 43 ；
Step S3, acquiring total pressure P of the outlet of the low-pressure turbine 5 ；
Step S4, determining the high-pressure turbine expansion ratio pi LH ：π LH ＝P 3 *σ 3-4 /(π TH *P 5 )。
Preferably, in step S1, a compressor outlet total pressure P is obtained 3 The method comprises the following steps: at the outlet of the compressorThe method comprises the steps of measuring pressure of a plurality of pressure points of the compressor at different cascade channels and different radial heights of an outlet of the compressor under the condition of the whole compressor by adopting an arc rake, and determining total pressure P of the outlet of the compressor according to the pressure points of the compressor 3 。
Preferably, in step S1, the compressor outlet total pressure P is determined according to the compressor pressure point pressure 3 The method comprises the following steps:
integrating the arc lengths of different radial heights of different cascade channels to obtain a total pressure arc length integral value;
taking the average value of the total pressure arc length integral values as the total pressure P of the outlet of the compressor 3 。
Preferably, the total arc length integral value is
Wherein n is the total pressure measurement point number, P 3-i-j-k Is the total pressure value of the kth measuring point, L i-j-k The arc length represented by the total pressure of the kth measuring point.
Preferably, in step S1, determining a main combustion chamber total pressure recovery coefficient includes: and when the Mach number of the outlet of the combustion chamber is smaller than a preset value, replacing the total pressure with the static pressure of the outlet of the combustion chamber to calculate the total pressure recovery coefficient of the main combustion chamber.
Preferably, the difference between the static pressure of the inner wall surface of the flame tube at the outlet of the main combustion chamber at different circumferential positions and the total pressure of the outlet of the compressor is arithmetically averaged to obtain the total pressure recovery coefficient of the main combustion chamber.
Preferably, the high pressure turbine outlet total pressure is measured through a sensing section made of a nickel-base superalloy material.
Preferably, a plurality of multi-point pressure sensing parts are adopted to measure the total pressure of the high-pressure turbine outlet and the total pressure of the low-pressure turbine outlet.
The high-low pressure turbine expansion ratio under the complete machine condition is obtained based on the actual measurement test data of the complete machine, so that more accurate evaluation results of the high-low pressure turbine expansion ratio under the complete machine condition can be obtained, and the method has important significance for realizing more accurate evaluation of the complete machine performance and the performance of the turbine component under the complete machine condition.
Drawings
FIG. 1 is a flow chart of a method for obtaining a high-low pressure turbo expansion ratio under the overall engine condition according to the present application.
FIG. 2 is a schematic cross-sectional view of an engine flowpath.
FIG. 3 is a schematic diagram of a compressor outlet total pressure measurement scheme.
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 method and the device have the advantages that the expansion ratios of the high-pressure turbine and the low-pressure turbine of the double-rotor turbofan engine under the condition of the whole engine are obtained, and the performance of the whole engine and the performance of the turbine part under the condition of the whole engine are more accurately evaluated.
As shown in fig. 1, the method for obtaining the expansion ratio of the high-pressure turbine and the low-pressure turbine under the condition of the whole engine mainly comprises the following steps:
step S1, obtaining total pressure P of outlet of compressor 3 Main combustion chamber total pressure recovery coefficient sigma 3-4 And total pressure P at the outlet of the high-pressure turbine 43 ；
Step S2, determining the high-pressure turbine expansion ratio pi TH ：π TH ＝P 3 *σ 3-4 /P 43 ；
Step S3, acquiring total pressure P of the outlet of the low-pressure turbine 5 ；
Step S4, determining the high-pressure turbine expansion ratio pi LH ：π LH ＝P 3 *σ 3-4 /(π TH *P 5 )。
Fig. 2 presents a schematic cross-sectional view of an engine flow path, wherein the parameters involved include: p 3 Is the average total pressure, sigma, of the compressor outlet 3-4 Recovery of the coefficient, P, for the total pressure in the main combustion chamber 43 Is the average total pressure, P, at the high-pressure turbine outlet (low-pressure turbine inlet) 5 The average total pressure of the low-pressure turbine outlet (inlet of a turbine rear casing support plate) is pi TH Is the high pressure turbo expansion ratio, pi LH Is the low pressure turbo expansion ratio. In order to obtain the expansion ratio of the high-pressure turbine and the low-pressure turbine under the complete machine condition of the double-rotor turbofan engine, in addition to measuring the total pressure of the outlet of the compressor, the total pressure recovery coefficient of the main combustion chamber, the total pressure of the outlet of the high-pressure turbine and the total pressure of the outlet of the low-pressure turbine are obtained, namely the total pressure recovery coefficient, the total pressure of 43 sections and the total pressure of 5 sections between 3 sections and 4 sections in fig. 2.
The method firstly needs to evaluate the feasibility of the measurement scheme, and carries out the feasibility evaluation of the measurement scheme according to the following steps:
1) carrying out interference check of a measurement scheme and an external pipeline/accessory of the engine based on an external digital model of the engine;
2) carrying out interference check on a measurement scheme and an engine bench based on an external digital model and a bench digital model of the engine;
3) and carrying out evaluation on the influence of the measurement scheme on the safety of the engine and the rack.
The measurement of the high-pressure turbine expansion ratio and the low-pressure turbine expansion ratio is carried out according to the following steps:
1) carrying out examination and test run of the sensed part, eliminating test bad points and ensuring the validity of the measured data;
2) according to P 43 The sensing part uses temperature limit to determine the limit value of the engine exhaust temperature, and if necessary (limited by the limit of the sensor working temperature), the sensing part enters at a lower atmospheric temperatureTests were conducted to reduce the temperature of the working environment of the sensitive part and prevent P 43 Ablation of the sensed part;
3) and the state of the engine is gradually improved in the test process, the expansion ratio of the high-pressure turbine is monitored in real time, and the state of the engine is not continuously improved after the expansion ratio of the high-pressure turbine is not increased any more, so that the test safety is ensured.
In some alternative embodiments, in step S1, the compressor outlet total pressure P is obtained 3 The method comprises the following steps: an arc-shaped rake is adopted at the outlet of the compressor, the pressure of a plurality of compressor pressure points with different cascade channels and different radial heights at the outlet of the compressor is measured under the condition of the whole compressor, and the total pressure P at the outlet of the compressor is determined according to the pressure of the compressor pressure points 3 。
In the embodiment, as shown in fig. 3, an arc rake is adopted at the outlet of the compressor, the pressures of different cascade channels and different radial heights at the outlet of the compressor are measured under the condition of the whole machine, and fig. 3 only shows the distribution of total pressure measuring points of one cascade channel in the circumferential direction, so that the distribution of an outlet pressure field considering the back trail of a stator at the outlet of the compressor is obtained, and the estimation precision of the average pressure at the outlet of the compressor is improved.
In some alternative embodiments, in step S1, the compressor outlet total pressure P is determined according to the compressor pressure point pressure 3 The method comprises the following steps:
integrating the arc lengths of different radial heights of different cascade channels to obtain a total pressure arc length integral value;
taking the average value of the total pressure arc length integral values as the total pressure P of the outlet of the compressor 3 。
In some alternative embodiments, the total arc length integrated value is
Wherein n is the total pressure measurement point number, P 3-i-j-k Is the total pressure value of the kth measuring point, L i-j-k Is the k-th testThe total dot pressure represents the arc length.
In the embodiment, the pressure values after the arc lengths of different radial heights of different cascade channels are integrated are subjected to arithmetic averaging to obtain more accurate section average pressure values considering the wake behind the stator at the outlet of the compressor.
In some alternative embodiments, determining the main combustor total pressure recovery coefficient in step S1 includes: and when the Mach number of the outlet of the combustion chamber is smaller than a preset value, replacing the total pressure with the static pressure of the outlet of the combustion chamber to calculate the total pressure recovery coefficient of the main combustion chamber.
In the embodiment, the main combustion chamber total pressure recovery coefficient is calculated by replacing the total pressure with the combustion chamber outlet static pressure, so that the performance evaluation precision requirement can be met.
In some optional embodiments, the difference between the static pressure of the inner wall surface of the flame tube at the main combustion chamber outlet position and the total pressure of the compressor outlet at different circumferential positions is subjected to arithmetic averaging to obtain the total pressure recovery coefficient of the main combustion chamber.
In this embodiment, the calculation formula is as follows:
wherein y is the number of differential pressure sensors, P 3 pressure difference-i And Δ P i And the total pressure value of the outlet of the compressor connected with the ith differential pressure sensor and the measured differential pressure value are respectively.
In some alternative embodiments, the high pressure turbine outlet total pressure is measured by a susceptor made of a nickel-base superalloy material.
In this embodiment, the total pressure at the outlet of the high-pressure turbine is measured by using the working characteristics that the high-pressure turbine guider reaches the critical state and the expansion ratio of the high-pressure turbine is basically unchanged when the engine is in a low rotating speed state, and by using the sensing part capable of bearing high temperature (for example, the sensing part made of a nickel-based high-temperature alloy material).
In some optional embodiments, according to the design flow field of the high-pressure turbine outlet and the low-pressure turbine outlet, the installation angles of the total pressure sensing parts of the high-pressure turbine outlet and the low-pressure turbine outlet and the air inlet angle of each measuring point on the sensing parts are determined, and a plurality of multi-point pressure sensing parts are adopted to measure high pressure and total pressure of the low-pressure turbine outlet
Designing a flow field according to a turbine outlet, correcting the total pressure measurement results of the turbine outlets of multiple points to obtain the total pressure average values of the high-pressure turbine outlet and the low-pressure turbine outlet which can represent the average pressure of the cross section, wherein the calculation formula is as follows:
P 43 measurement And P 5 measurement of Respectively the average value of each total pressure measuring point of the high-pressure turbine outlet and the low-pressure turbine outlet, P 43 design And P 5 design Designing total pressure average values of total pressure measuring point positions of a flow field for the outlets of the high-pressure turbine and the low-pressure turbine respectively,
and
and designing the total pressure average value of the flow field section for the high-pressure turbine outlet and the low-pressure turbine outlet respectively.
The high-low pressure turbine expansion ratio under the complete machine condition is obtained based on the actual measurement test data of the complete machine, so that more accurate evaluation results of the high-low pressure turbine expansion ratio under the complete machine condition can be obtained, and the method has important significance for realizing more accurate evaluation of the complete machine performance and the performance of the turbine component under the complete machine condition.
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 (6)
1. A method for obtaining the expansion ratio of a high-pressure turbine and a low-pressure turbine under the condition of the whole engine is characterized by comprising the following steps:
step S1, obtaining total pressure P of outlet of compressor 3 Main combustion chamber total pressure recovery coefficient sigma 3-4 And total pressure P at the outlet of the high-pressure turbine 43 ；
Step S2, determining the high-pressure turbine expansion ratio pi TH ：π TH ＝P 3 *σ 3-4 /P 43 ；
Step S3, acquiring total pressure P of the outlet of the low-pressure turbine 5 ；
Step S4, determining the high-pressure turbine expansion ratio pi LH ：π LH ＝P 3 *σ 3-4 /(π TH *P 5 )；
In step S1, determining the compressor outlet total pressure P according to the compressor pressure point pressure 3 The method comprises the following steps:
integrating the arc lengths of different radial heights of different cascade channels to obtain an integral value of the total pressure arc length;
taking the average value of the total pressure arc length integral values as the total pressure P of the outlet of the compressor 3 ；
The total pressure arc length integral value is
Wherein n is the total pressure measurement point number, P 3-i-j-k Is the total pressure value of the kth measuring point, L i-j-k The arc length represented by the total pressure of the kth measuring point.
2. The method for obtaining the expansion ratio of the high-low pressure turbine under the condition of the whole engine as claimed in claim 1, wherein in step S1, the total pressure P of the outlet of the compressor is obtained 3 The method comprises the following steps: an arc-shaped rake is adopted at the outlet of the compressor, the pressure of a plurality of compressor pressure points with different cascade channels and different radial heights at the outlet of the compressor is measured under the condition of the whole compressor, and the total pressure P at the outlet of the compressor is determined according to the pressure of the compressor pressure points 3 。
3. The method for obtaining the turbo expansion ratio under the condition of the whole engine as claimed in claim 1, wherein the step S1 of determining the main combustion chamber total pressure recovery coefficient includes: and when the Mach number of the outlet of the combustion chamber is smaller than a preset value, replacing the total pressure with the static pressure of the outlet of the combustion chamber to calculate the total pressure recovery coefficient of the main combustion chamber.
4. The method for obtaining the expansion ratio of the high-low pressure turbine under the condition of the complete engine as claimed in claim 3, wherein the difference between the static pressure of the inner wall surface of the flame tube at the position of the main combustion chamber outlet and the total pressure of the compressor outlet at different circumferential positions is subjected to arithmetic averaging to obtain the total pressure recovery coefficient of the main combustion chamber.
5. The method for obtaining the expansion ratio of the high-pressure turbine and the low-pressure turbine under the condition of the whole engine as claimed in claim 1, wherein the total pressure of the outlet of the high-pressure turbine is measured by an inductive part made of a nickel-based superalloy material.
6. The method for obtaining the expansion ratio of the high-pressure turbine and the low-pressure turbine under the condition of the whole engine as claimed in claim 1, wherein the total pressure of the outlet of the high-pressure turbine and the total pressure of the outlet of the low-pressure turbine are measured by a plurality of multipoint pressure sensing parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110678694.4A CN113221294B (en) | 2021-06-18 | 2021-06-18 | Method for obtaining expansion ratio of high-low pressure turbine under engine complete machine condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110678694.4A CN113221294B (en) | 2021-06-18 | 2021-06-18 | Method for obtaining expansion ratio of high-low pressure turbine under engine complete machine condition |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113221294A CN113221294A (en) | 2021-08-06 |
| CN113221294B true CN113221294B (en) | 2022-09-20 |
Family
ID=77080490
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110678694.4A Active CN113221294B (en) | 2021-06-18 | 2021-06-18 | Method for obtaining expansion ratio of high-low pressure turbine under engine complete machine condition |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113221294B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114065661B (en) * | 2021-11-10 | 2022-09-20 | 中国航发沈阳发动机研究所 | Method and system for evaluating loss of rear turbine casing under engine complete machine condition |
| CN115356115B (en) * | 2022-10-24 | 2023-03-07 | 中国航发四川燃气涡轮研究院 | Layout method for mainstream flow field fine test in core machine environment |
| CN115901268A (en) * | 2022-11-08 | 2023-04-04 | 中国航发沈阳发动机研究所 | Method for accurately acquiring total pressure loss coefficient of combustion chamber on engine |
| CN116595790B (en) * | 2023-05-26 | 2024-06-14 | 中国航发沈阳发动机研究所 | Accurate determination method for low-conductance capacity requirement of whole engine |
| CN116658451B (en) * | 2023-08-02 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Method for correcting total pressure of outlet of air compressor in core machine environment based on wake loss |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111914362A (en) * | 2020-07-22 | 2020-11-10 | 中国航发沈阳发动机研究所 | Self-adaptive method for turbofan engine model in research and development stage |
| CN112550758A (en) * | 2020-12-03 | 2021-03-26 | 中国航发沈阳发动机研究所 | Method for obtaining actual performance of each part of engine under complete machine condition |
-
2021
- 2021-06-18 CN CN202110678694.4A patent/CN113221294B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111914362A (en) * | 2020-07-22 | 2020-11-10 | 中国航发沈阳发动机研究所 | Self-adaptive method for turbofan engine model in research and development stage |
| CN112550758A (en) * | 2020-12-03 | 2021-03-26 | 中国航发沈阳发动机研究所 | Method for obtaining actual performance of each part of engine under complete machine condition |
Non-Patent Citations (1)
| Title |
|---|
| 1+3/2级对转涡轮气动性能试验研究;吴中野等;《北京航空航天大学学报》(第12期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113221294A (en) | 2021-08-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113221294B (en) | Method for obtaining expansion ratio of high-low pressure turbine under engine complete machine condition | |
| CN112550758B (en) | Method for obtaining actual performance of each part of engine under complete machine condition | |
| CN112067304B (en) | Method for measuring inlet flow of compressor in engine whole machine test | |
| CN110717219A (en) | Method and device for acquiring inlet flow of compressor in complete state of aircraft engine | |
| CN110043370B (en) | Air flow measuring method of turbofan engine core machine | |
| CN109632325B (en) | Main combustion chamber flow distribution method | |
| Lengyel-Kampmann et al. | Design of an economical counter rotating fan: comparison of the calculated and measured steady and unsteady results | |
| Klausmann et al. | Transonic compressor Darmstadt—Open test case | |
| CN113405805A (en) | Aero-engine inlet flow obtaining method considering boundary layer of air inlet channel | |
| CN113361040B (en) | Combustion chamber outlet temperature evaluation method under complete engine condition | |
| CN114065661B (en) | Method and system for evaluating loss of rear turbine casing under engine complete machine condition | |
| Anthony et al. | Phantom cooling effects on rotor blade surface heat flux in a transonic full scale 1+ 1/2 stage rotating turbine | |
| CN115901268A (en) | Method for accurately acquiring total pressure loss coefficient of combustion chamber on engine | |
| CN115356115B (en) | Layout method for mainstream flow field fine test in core machine environment | |
| CN108760329B (en) | Low-pressure turbine noise test method and improvement method thereof | |
| Bryce et al. | Three-dimensional flow in a highly loaded single-stage transonic fan | |
| CN115356027A (en) | High-pressure turbine efficiency evaluation method and device based on low-pressure shaft power balance | |
| CN108197342B (en) | Method for calculating non-design air leakage of air system of aircraft engine | |
| CN115163330B (en) | Method for determining stability boundary of compression system of double-bypass core machine | |
| Takakura | Entropy generation in the tip region of a high-pressure turbine | |
| CN112179665B (en) | Method for acquiring inlet stagnation pressure of low-pressure turbine performance test | |
| CN114720145A (en) | Low-pressure turbine performance test method with rectifying blades | |
| Key et al. | An experimental study of vane clocking effects on embedded compressor stage performance | |
| CN115587490A (en) | Method for analyzing thermal state relative position relationship of grate of air system of aircraft engine | |
| Cernat et al. | Experimental investigation of a high-speed turbine with rainbow rotor and rim seal purge flow |
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 |