CN115688319A - Variable cycle compression system test matching characteristic modeling method - Google Patents
Variable cycle compression system test matching characteristic modeling method Download PDFInfo
- Publication number
- CN115688319A CN115688319A CN202211401355.2A CN202211401355A CN115688319A CN 115688319 A CN115688319 A CN 115688319A CN 202211401355 A CN202211401355 A CN 202211401355A CN 115688319 A CN115688319 A CN 115688319A
- Authority
- CN
- China
- Prior art keywords
- characteristic
- compression system
- bypass
- dimensionless
- variable cycle
- 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
Links
Images
Classifications
-
- 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
Abstract
The application provides a variable cycle compression system test matching characteristic modeling method, which comprises the following steps: establishing a pneumatic performance surface area characteristic diagram of the variable cycle compression system, wherein the abscissa of the pneumatic performance surface area characteristic diagram is the converted flow of the variable cycle compression system, and the ordinate of the pneumatic performance surface area characteristic diagram is the bypass ratio or dimensionless bypass back pressure; extracting a key element curve from the pneumatic performance area characteristic diagram; determining a bypass ratio or a bypass dimensionless backpressure range to be analyzed in the aerodynamic performance surface area characteristic diagram; extracting a plurality of characteristic curves of the aerodynamic performance of the compressor or the fan from a blocking point to a surge point when the bypass ratio or the dimensionless back pressure is not changed along the fixed condition of the characteristic parameters within the range of the bypass ratio or the dimensionless back pressure of the bypass; extracting a working point characteristic parameter, a surge point characteristic parameter and a surge margin of each compressor or fan aerodynamic performance characteristic curve; and respectively establishing a change curve of the working point characteristic parameter, the surge point characteristic parameter and the surge margin along with the bypass ratio or the bypass dimensionless back pressure, and fitting.
Description
Technical Field
The application belongs to the technical field of aero-engines, and particularly relates to a modeling method for testing matching characteristics of a variable cycle compression system.
Background
The adaptive variable-cycle engine has multiple working modes and complex characteristics, and the compression parts of the engine can comprise a three-duct adaptive fan and a variable-cycle double-duct compressor. In order to meet the requirements of multiple working modes of the whole engine, compared with a conventional fan or a compressor, the pneumatic performance and the structure of a compression system or a component of the self-adaptive variable-cycle engine are greatly changed.
As shown in fig. 1, the adaptive tri-ducted fan 10 includes adjustable blades 11, a front fan rotor 12, a front fan stator 13, a rear fan rotor 14, and a rear fan stator 16 in sequence, wherein a duct is provided between the front fan stator 13 and the rear fan rotor 14, the duct forms a third duct 19, a splitter ring 17 is provided behind the rear fan stator 16, and the splitter ring 17 divides a main flow path of the fan into an inner duct 16 and an outer duct 18, thereby forming a tri-ducted structure.
As shown in fig. 2, a typical variable-cycle dual-duct compressor 20 includes adjustable blades 21, a core driving fan rotor 22, a core driving fan stator 23, a compressor rotor 24, and a compressor stator 25 in sequence, a duct is provided between the core driving fan stator 23 and the compressor rotor 24, the duct forms a front duct 27, and a compressor outlet 26 is provided at the rear side of the compressor stator 25 to form a rear duct.
As shown in fig. 3, the third duct environmental backpressure has a strong coupling characteristic with the third duct/front duct aerodynamic environment, so that the performance of the fan or the compressor changes in a wide range in different matching states, which optimizes the performance of the adaptive fan and the variable cycle compressor, and especially brings great technical problems to matching and use of each component in the whole engine. At present, because the self-adaptive compression system is greatly influenced by the characteristics of the duct, the component test is usually carried out on the pneumatic performance test measurement aiming at the states of a small number of ducts, the pneumatic performance test measurement is mainly used for verifying simulation calculation, effective means is lacked, the component test is passed, and a method for effectively supporting the matching of the component performance under the working environment of the whole machine based on the component test data is directly established.
Disclosure of Invention
It is an object of the present application to provide a method of modeling a test matching characteristic of a variable cycle compression system that solves or mitigates at least one of the problems of the background art.
The technical scheme of the application is as follows: a modeling method for testing matching characteristics of a variable cycle compression system comprises the following steps:
establishing a pneumatic performance surface area characteristic diagram of the variable cycle compression system, wherein the abscissa of the pneumatic performance surface area characteristic diagram is the converted flow of the variable cycle compression system, the ordinate of the pneumatic performance surface area characteristic diagram is a characteristic parameter of a third duct of the self-adaptive three-duct fan or a front duct of the variable cycle compressor, and the characteristic parameter is a duct ratio or dimensionless duct back pressure;
extracting a key element curve from the pneumatic performance area characteristic diagram of the variable cycle compression system;
determining a bypass ratio or a bypass dimensionless backpressure range to be analyzed in the aerodynamic performance surface area characteristic diagram;
extracting a plurality of aerodynamic performance characteristic curves of the compressor or the fan from a blocking point to a surge point when the bypass ratio or the dimensionless back pressure is not changed along with the fixed characteristic parameters within the range of the bypass ratio or the dimensionless back pressure of the bypass;
extracting a working point characteristic parameter, a surge point characteristic parameter and a surge margin of each compressor or fan aerodynamic performance characteristic curve;
and respectively establishing a change curve of the working point characteristic parameter, the surge point characteristic parameter and the surge margin along with the bypass ratio or the bypass dimensionless back pressure, and fitting a model to obtain a pneumatic performance characteristic curve matched with the variable-cycle compression system.
Further, the key element curves include a working line, a maximum efficiency line or a maximum pressure ratio line and a surge boundary line.
Furthermore, the extracted aerodynamic performance characteristic curves of the compressor or the fan are not less than 4.
Further, the operating point characteristic parameters and the surge point characteristic parameters comprise pressure ratio, flow rate and efficiency.
Further, the fitting process adopts a quadratic relation: f = m (B) 2 +n(B)+p
Where F is a compression system characteristic parameter, B is a bypass ratio or a dimensionless back pressure, and m, n, and p are coefficients that vary depending on a test object and a rotation speed state.
The method can establish a model of the influence of the bypass variable based on the test data of the part on the pneumatic performance of the adaptive compression system, thereby quantitatively evaluating the change rule of the performance parameters of key states such as the working point, surge and the like of the compression system along with the characteristic variables such as the bypass ratio and the like, and effectively guiding the matching regulation and use of the part under the condition of the whole aircraft engine.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
Fig. 1 is a schematic diagram of a self-adaptive three-duct fan structure.
Fig. 2 is a schematic structural diagram of a variable-cycle dual-duct compressor.
Fig. 3 is a schematic diagram illustrating an influence of the third-duct environmental backpressure on the performance of the adaptive three-duct fan according to an embodiment.
Fig. 4 is a flowchart of a modeling method for testing matching characteristics of a variable cycle compression system according to the present application.
FIG. 5 is a schematic view of the aerodynamic performance area characteristics established according to an embodiment of the present application.
FIG. 6 is a compression system characteristic curve extracted along a fixed-duct feature variable in an 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 drawings in the embodiments of the present application.
Aiming at the problem that the performance of a part is matched and the supporting strength is good under the whole machine working environment by the current part test data, the application provides a modeling method for the test matching characteristic of a variable cycle gas compression system based on the part test data drive, and the matching problem of the self-adaptive compression system under the whole machine working environment is solved.
As shown in fig. 4, the method for developing adaptive compression system matching characteristic modeling based on test performance provided by the present application includes the following steps:
s1, establishing a surface area characteristic diagram representing the aerodynamic performance of the adaptive variable-cycle compression system through a test method to form an aerodynamic performance surface area 30 of the adaptive variable-cycle compression system, wherein as shown in FIG. 5, the abscissa of the aerodynamic performance surface area characteristic diagram is the converted flow m of the adaptive variable-cycle compression system, and the ordinate of the aerodynamic performance surface area characteristic diagram is a characteristic parameter of a third duct of the adaptive three-duct fan or a front duct of the variable-cycle compressor, namely a duct ratio or a dimensionless duct back pressure B.
S2, extracting key element curves from the pneumatic performance area characteristic diagram, wherein the key element curves comprise a working line 31, a maximum efficiency line/maximum pressure ratio line 32 and a surge boundary line 33 as shown in FIG. 5;
and S3, determining a ducted ratio or a ducted dimensionless backpressure range which needs to be subjected to emphasis analysis in the surface region characteristic diagram, wherein the ducted ratio or the ducted dimensionless backpressure range which is subjected to emphasis analysis in the surface region characteristic diagram is a range between a fixed-vertical-coordinate ducted characteristic variable curve 34 and a fixed-vertical-coordinate ducted characteristic variable curve 35 as shown in FIG. 5.
And S4, in the determined bypass ratio or the dimensionless back pressure range of the bypass, extracting not less than 4 bypass ratios or compressor or fan aerodynamic performance characteristic curves from a blocking point to a surge point under the condition of constant dimensionless back pressure along a fixed bypass characteristic variable, wherein the bypass ratio or dimensionless back pressure when each compressor or fan aerodynamic performance characteristic curve is extracted covers the concerned parameter range as uniformly as possible. As shown in fig. 5, the fixed duct characteristic variable curve 36 is an extracted compressor or fan aerodynamic performance characteristic curve, and fig. 6 shows a plurality of compressor or fan aerodynamic performance characteristic curves extracted and converted through the above process.
S5, extracting working point characteristic parameters (pressure ratio, flow and efficiency), surge margin and the like of each pneumatic performance characteristic curve of the compressor or the fan;
s6, respectively establishing a change curve of the working point characteristic parameters (pressure ratio, flow and efficiency), the surge point characteristic parameters (pressure ratio, flow and efficiency) and the surge margin along with the bypass ratio or the dimensionless back pressure of the bypass, and fitting a model, wherein the fitting process adopts a quadratic relation:
F＝m(B) 2 +n(B)+p
where F is a compression system characteristic parameter, such as: operating point characteristics (pressure ratio, flow, efficiency), surge point characteristics (pressure ratio, flow, efficiency), or surge margin; b is the bypass ratio or dimensionless back pressure; m, n, and p are coefficients that vary depending on the test object and the rotational speed state.
S7, analyzing the reasonability of the model, for example, increasing the number of the extracted characteristic lines to check the change of the rule of the model, and repeating the steps S2 to S6 if the analysis requirement is not met.
The method can establish a model of influence of the bypass variable based on the test data of the part on the pneumatic performance of the adaptive compression system, so that the change rule of the performance parameters of key states such as the working point, surge and the like of the compression system along with characteristic variables such as the bypass ratio and the like is quantitatively evaluated, and the matching regulation and use of the part under the condition of the whole aircraft engine are effectively guided.
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 (5)
1. A modeling method for testing matching characteristics of a variable cycle compression system is characterized by comprising the following steps:
establishing a pneumatic performance surface area characteristic diagram of the variable cycle compression system, wherein the abscissa of the pneumatic performance surface area characteristic diagram is the converted flow of the variable cycle compression system, the ordinate is a characteristic parameter of a third duct of the self-adaptive three-duct fan or a front duct of the variable cycle compressor, and the characteristic parameter is a duct ratio or dimensionless duct back pressure;
extracting a key element curve from the pneumatic performance area characteristic diagram of the variable cycle compression system;
determining a bypass ratio or a bypass dimensionless backpressure range to be analyzed in the aerodynamic performance surface area characteristic diagram;
extracting a plurality of aerodynamic performance characteristic curves of the compressor or the fan from a blocking point to a surge point when the bypass ratio or the dimensionless back pressure is not changed along with the fixed characteristic parameters within the range of the bypass ratio or the dimensionless back pressure of the bypass;
extracting a working point characteristic parameter, a surge point characteristic parameter and a surge margin of each compressor or fan aerodynamic performance characteristic curve;
and respectively establishing a change curve of the working point characteristic parameter, the surge point characteristic parameter and the surge margin along with the bypass ratio or the bypass dimensionless back pressure, and fitting a model to obtain a pneumatic performance characteristic curve matched with the variable-cycle compression system.
2. The method of modeling test matching characteristics for a variable cycle compression system according to claim 1, wherein the key element curves include a working line, a peak efficiency line or a peak pressure ratio line and a surge boundary line.
3. The variable cycle compression system test matching characteristic modeling method of claim 1, wherein the extracted compressor or fan aerodynamic performance characteristic curves are not less than 4.
4. The method of modeling trial matching characteristics of a variable cycle compression system as claimed in claim 1, wherein said operating point characteristic parameters and chubby point characteristic parameters include pressure ratio, flow rate, efficiency.
5. The modeling method for experimental matching characteristics of a variable cycle compression system of claim 4, wherein the fitting process uses a quadratic relation: f = m (B) 2 +n(B)+p
Where F is a compression system characteristic parameter, B is a bypass ratio or a dimensionless back pressure, and m, n, and p are coefficients that vary depending on a test object and a rotation speed state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211401355.2A CN115688319A (en) | 2022-11-09 | 2022-11-09 | Variable cycle compression system test matching characteristic modeling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211401355.2A CN115688319A (en) | 2022-11-09 | 2022-11-09 | Variable cycle compression system test matching characteristic modeling method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115688319A true CN115688319A (en) | 2023-02-03 |
Family
ID=85050365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211401355.2A Pending CN115688319A (en) | 2022-11-09 | 2022-11-09 | Variable cycle compression system test matching characteristic modeling method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115688319A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116151157A (en) * | 2023-04-23 | 2023-05-23 | 中国航发四川燃气涡轮研究院 | Calculation method for simulating surge hammering wave load of engine |
-
2022
- 2022-11-09 CN CN202211401355.2A patent/CN115688319A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116151157A (en) * | 2023-04-23 | 2023-05-23 | 中国航发四川燃气涡轮研究院 | Calculation method for simulating surge hammering wave load of engine |
| CN116151157B (en) * | 2023-04-23 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Calculation method for simulating surge hammering wave load of engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110929357A (en) | Pneumatic design method for high-performance ship gas turbine compressor | |
| Graf et al. | Effects of nonaxisymmetric tip clearance on axial compressor performance and stability | |
| US10352330B2 (en) | Turbomachine part with a non-axisymmetric surface | |
| CN115688319A (en) | Variable cycle compression system test matching characteristic modeling method | |
| Tsoutsanis et al. | An efficient component map generation method for prediction of gas turbine performance | |
| CN109815624A (en) | A kind of compressor stability boundaris judgment method for considering inlet total pressure distortion and influencing | |
| Yue et al. | Design and optimization of tandem arranged cascade in a transonic compressor | |
| CN114444331A (en) | Stage characteristic matching method of multistage axial flow compressor | |
| Cravero et al. | Numerical prediction of tonal noise in centrifugal blowers | |
| Bakhtiari et al. | Design and optimization of a new stator for the transonic compressor rig at TU darmstadt | |
| Hall et al. | Performance prediction of endwall treated fan rotors with inflow distortion | |
| CN107991200B (en) | Fatigue life prediction method for titanium alloy impeller | |
| CN112632726B (en) | Flow field reconstruction method for aeroelastic simulation of impeller mechanical blade | |
| CN115577453A (en) | Variable pitch propeller pneumatic design method, device and system | |
| CN114812994A (en) | Method for identifying dynamic vibration measurement mode of aero-engine blade based on inner product correlation | |
| CN115587286A (en) | Performance characterization method of variable cycle compression system | |
| Patel et al. | CFD analysis of mixed flow pump | |
| CN111950377A (en) | Rotary machine fault intelligent diagnosis method based on fuzzy soft morphological pattern recognition | |
| CN115186443B (en) | Pneumatic design method for multistage power turbine of power generation type gas turbine for inverted bathtub load ship | |
| Moyle | Analysis of Efficiency Sensitivity Associated with Tip Clearance in Axial Flow Compressors | |
| CN113137282B (en) | Reaction turbine stage group connection structure and structural parameter design method thereof | |
| CN116090265B (en) | Quantitative evaluation method for pressure pulsation intensity of variable-speed pumped storage unit | |
| Doroshenko et al. | Research into aero acoustic characteristics of two-row impellers of the axial compressor | |
| CN111336003B (en) | Method for positioning key influence factors of turbocharging system of aircraft engine | |
| CN113792503B (en) | Low-working-condition interstage deflation anti-surge method for low-pressure compressor of marine gas turbine |
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 |