CN115307924A

CN115307924A - Dynamic ground effect simulation system for shipborne test run of aircraft engine

Info

Publication number: CN115307924A
Application number: CN202211244139.1A
Authority: CN
Inventors: 陈鹏飞; 黄维娜; 杨华; 刘志友; 王衡; 杨斐; 巩鑫; 李晓明
Original assignee: AECC Sichuan Gas Turbine Research Institute
Current assignee: AECC Sichuan Gas Turbine Research Institute
Priority date: 2022-10-12
Filing date: 2022-10-12
Publication date: 2022-11-08
Anticipated expiration: 2042-10-12
Also published as: CN115307924B

Abstract

The invention provides a ship-borne test run dynamic ground effect simulation system of an aircraft engine, which comprises a three-degree-of-freedom lifting platform, wherein the three-degree-of-freedom lifting platform comprises: the first plane base layer, the second plane base layer, the third plane base layer and the fourth plane base layer; the lifting assembly is arranged on the first plane base layer, the second plane base layer is fixedly arranged at the upper end of the lifting assembly, and the second plane base layer can be lifted along the first direction relative to the first plane base layer along with the lifting assembly; the second direction rotating assembly is arranged above the second planar base layer, the third planar base layer is connected with the second direction rotating assembly, and the third planar base layer can rotate relative to the second planar base layer in the second direction; the third direction rotating assembly is arranged above the third plane base layer, the fourth plane base layer is connected with the third direction rotating assembly, the fourth plane base layer can rotate relative to the third plane base layer in the third direction, and the first direction, the second direction and the third direction are perpendicular to each other.

Description

Dynamic ground effect simulation system for shipborne test run of aircraft engine

Technical Field

The invention relates to the technical field of aircraft engines, in particular to a shipborne test run dynamic ground effect simulation system of an aircraft engine.

Background

The simulation of the pneumatic flow field for test run under the unstable plane air inlet condition is the key for solving the real ship-based test run risk of the aircraft engine and obtaining the dynamic ground effect pneumatic characteristic. The traditional aircraft engine test vehicle is mainly developed on a fixed indoor test vehicle table or an open-air test vehicle table, the physical state of an engine air inlet flow field and the ground is constant, but with the arrangement of the aircraft engine on a ship, the engine can develop test vehicle work on the ship, and due to the continuous action of ocean wind and waves, the ship body can continuously perform three-degree-of-freedom deflection and vertical fluctuation movement, and then dynamic interference is generated on the air flow of the engine test vehicle air inlet flow field. In addition, due to spatial nonuniformity caused by the ground-near effect, a complex flow rule is formed in an air inlet flow field of the ship-based test run, and even the phenomenon that an engine is damaged by being sucked by an external object can occur under the conditions of low ground clearance and severe sea conditions of the engine test run, so that the test run performance and the running safety of the engine are seriously influenced.

The method for researching and obtaining the aerodynamic characteristics of the ship-based test run at the present stage mainly carries out dynamic simulation and multi-scale eddy current calculation by a numerical simulation method, but the method lacks effective simulation correction and verification; the other method is to actually measure the aerodynamic characteristics of the dynamic ground effect by a traditional static ground test and matching with different crosswind incoming flow methods, but the method is a simplified variable air intake scene and cannot effectively evaluate the coupling effect of the carrier-based dynamic ground and the non-uniform airflow.

Disclosure of Invention

In view of this, the embodiment of the invention provides a dynamic ground effect simulation system for a ship-based test run of an aircraft engine, so as to ensure the pneumatic performance and safety of the ship-based test run of the aircraft engine.

The specific scheme of the invention is as follows: the utility model provides an aircraft engine carrier-borne dynamic ground effect analog system that tries on a trial run, includes three degree of freedom lift platforms, and three degree of freedom lift platforms include: the first plane base layer, the second plane base layer, the third plane base layer and the fourth plane base layer; the lifting assembly is arranged on the first plane base layer, the second plane base layer is fixedly arranged at the upper end of the lifting assembly, and the second plane base layer can be lifted along the first direction relative to the first plane base layer along with the lifting assembly; the second direction rotating assembly is arranged above the second planar base layer, the third planar base layer is connected with the second direction rotating assembly, and the third planar base layer can rotate relative to the second planar base layer in the second direction; the third direction rotating assembly is arranged above the third plane base layer, the fourth plane base layer is connected with the third direction rotating assembly, the fourth plane base layer can rotate relative to the third plane base layer in the third direction, and the first direction, the second direction and the third direction are perpendicular to each other.

Furthermore, the aircraft engine carrier-based test run dynamic ground effect simulation system further comprises a rack mounting assembly, the rack mounting assembly is of a box-shaped structure with an inner cavity, and the three-degree-of-freedom lifting platform is arranged on the lower bottom surface of the rack mounting assembly.

Furthermore, the aircraft engine carrier-based test run dynamic ground effect simulation system further comprises a simulation bench and an air inlet test assembly, and the simulation bench and the air inlet test assembly are arranged on the upper top surface of the bench installation assembly.

Further, simulation rack and test assembly that admits air includes: the simulation engine is fixedly connected with the upper top surface of the rack mounting assembly through an engine moving frame mounting plate; and one end of the air supply pipe is connected with the simulation engine for air supply, and the other end of the air supply pipe is arranged on the outer side of the top surface of the upper top surface of the rack mounting assembly.

Further, simulation rack and test assembly that admits air still includes: the process air inlet channel is connected with one end of the simulation engine and is connected with the upper top surface of the rack mounting assembly through the flow tube mounting plate; one end of the process air inlet channel rotating assembly is connected with the process air inlet channel, the other end of the process air inlet channel rotating assembly is arranged on the outer side of the top surface of the upper top surface of the rack mounting assembly, and the process air inlet channel rotating assembly can drive the process air inlet channel to rotate relative to the simulation engine.

Furthermore, a pulsating pressure measuring device and a temperature and pressure measuring device are arranged on the process air inlet channel.

Furthermore, a plurality of mounting holes are formed in the upper top surface of the rack mounting assembly and are uniformly distributed at intervals in the second direction, and the simulation rack and the air inlet testing assembly can be selectively and fixedly connected with one of the mounting holes.

Further, rack installation component includes the stand that many intervals set up, and rack installation component's last top surface and rack installation component's lower bottom surface all are connected with the stand.

Furthermore, the upper end and the lower end of each stand column are provided with adjusting holes for adjusting the mounting positions of the upper top surface of the rack mounting assembly and the lower bottom surface of the rack mounting assembly.

And further, a smoke generator and a static pressure measuring point are arranged on the three-degree-of-freedom lifting platform.

Compared with the prior art, the at least one technical scheme adopted by the embodiment of the invention can achieve the beneficial effects of at least:

the invention can realize the function simulation of air inlet of the engine at different ground clearance heights, and can equivalently simulate the static ground effect aerodynamic characteristics of the engine at different magnitudes through the dimensionless ratio of the diameter of the process air inlet channel to the ground clearance height.

The three-degree-of-freedom lifting platform can perform equivalent dynamic simulation according to the three-degree-of-freedom deflection and vertical fluctuation motion conditions of the ship body in the marine environment, and the servo control precision is high.

The cross section of the process air inlet channel can be measured by rotating the manual screw rod for 180 degrees, all air inlet cross section air flow parameters are measured, the operation is convenient, and the reliability is high.

The three-free-plane smoke generating device and the static pressure measuring point can effectively evaluate the ground vortex condition generated by the ground effect, the visualization effect is good, and the three-free-plane smoke generating device is particularly suitable for evaluating the ground vortex in a simulation experiment.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a front view of an embodiment of the present invention;

FIG. 2 is a schematic three-dimensional structure of an embodiment of the present invention;

FIG. 3 is a schematic diagram of the simulation bench and the air intake test assembly;

fig. 4 is a schematic front view structure diagram of the three-degree-of-freedom lifting platform;

FIG. 5 is a schematic diagram of a three-dimensional structure of a three-degree-of-freedom lifting platform;

fig. 6 is a partial schematic view of a three-degree-of-freedom lifting platform.

Reference numbers in the figures:

1. a rack mount assembly; 11. an upper cross beam; 12. a column; 13. a rack bottom surface; 15. a thrust measurement assembly; 14. an upper mounting surface of the rack;

2. a simulation bench and an air inlet test assembly; 21. a rack moving frame mounting plate; 22. an auxiliary cross-section mounting plate; 23. a main section mounting plate; 24. a flow tube mounting plate; 25. simulating an engine; 26. a process inlet duct rotating assembly; 27. a process inlet duct measuring section; 28. a process inlet duct convergence section; 29. a pulsating pressure measuring device; 210. a temperature and pressure measuring device;

3. a three-degree-of-freedom lifting platform; 31. a fourth planar base layer; 32. a smoke generator; 33. measuring a static pressure point; 34. a first hinge support; 35. a second hinge support; 36. a third planar base layer; 37. a third hinge support; 38. a fourth hinge support; 39. a fifth hinge support; 310. an x-direction servo rolling actuator cylinder; 311. an x-direction roll indicator; 312. a rolling limiting device in the x direction; 313. a sixth hinge support; 314. a ninth hinge support; 315. a seventh hinged support; 316. a tenth hinge support; 317. a y-direction roll indicator; 318. a y-direction rolling limiting device; 319. a second planar base layer; 320. an eighth hinged support; 321. a y-direction servo rolling actuator cylinder; 322. a first planar base layer; 323. a first slide rail; 324. a second slide rail; 325. a third slide rail; 326. a fourth slide rail; 327. a z-direction servo lift ram.

Detailed Description

The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and variations in various respects, all without departing from the spirit of the present application. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

As shown in fig. 1 to 6, an aircraft engine carrier-based test run dynamic ground effect simulation system provided in an embodiment of the present invention includes a gantry mounting assembly 1, a simulation gantry, an air intake testing assembly 2, and a three-degree-of-freedom lifting platform 3.

The rack mounting assembly 1 consists of an upper cross beam 11, a vertical column 12, a rack bottom surface 13, a rack upper mounting surface 14 and a thrust measuring assembly 15. Wherein 4 stands 12 and 4 entablature 11 constitute rack installation frame, entablature 11 can realize the simulation of the different air inlet height of engine through the different installation position of stand 12, rack bottom surface 13 is installed in stand 12 below, the simulation naval vessel engine air inlet plane, rack upper mounting face 14 is installed on 4 entablature 11, it has the regulation hole to open on it, can realize engine position adjustment around admitting air through the regulation hole, thrust measurement subassembly 15 is installed under rack upper mounting face 14, thrust measurement subassembly is by the static frame of rack, the spring leaf, thrust measurement subassembly is constituteed, can realize carrying on the accurate measurement to engine steady state and transition state thrust under the dynamic ground effect of carrier-borne test. The rack mounting assembly 1 simulates the rack mounting conditions under the ship-borne conditions, can realize the mounting of engine racks with different air inlet heights and different air inlet distances, and can accurately measure the steady-state thrust and the transitional-state thrust of an engine.

The simulation bench and air inlet test component 2 comprises a bench moving rack mounting plate 21, an auxiliary section mounting plate 22, a main section mounting plate 23, a flow pipe mounting plate 24, a simulation engine 25, a process air inlet channel rotating component 26, a process air inlet channel measuring section 27, a process air inlet channel converging section 28, a pulsating pressure measuring device 29 and a temperature and pressure measuring device 210. The bench moving frame mounting plate 21 is mounted on the thrust measuring assembly 15 and transmits the engine thrust to the thrust measuring assembly 15, the auxiliary mounting section of the engine is fixed on the lower side of the auxiliary section mounting plate 22, the upper side of the auxiliary section mounting plate is mounted on the bench moving frame mounting plate 21, the main mounting section of the engine is fixed on the lower side of the main section mounting plate 23, the upper side of the auxiliary section mounting plate is mounted on the bench moving frame mounting plate 21 and transmits the engine thrust to the bench moving frame mounting plate 21, the upper side of the flow tube mounting plate 24 is mounted on the bench moving frame mounting plate 21, the flow tube is fixed on the lower side of the flow tube mounting plate and simulates the working conditions of the engine 25 in different flows and different states by adjusting power, the process air inlet channel rotating assembly 26 drives the process air inlet channel measuring section 27 to rotate through a hand wheel, a connecting rod and a transmission mechanism, flow field parameters of all positions in the cross section can be measured, the process air inlet channel converging section 28 is connected in front of the process air inlet channel measuring section 27 to ensure the quality of an air inlet flow field, the pulsating pressure measuring device 29 is arranged on the process air inlet channel measuring section 27 and used for measuring the total pulsating pressure and the static pressure of an engine inlet, and the temperature and pressure measuring device 210 is arranged on the process air inlet channel measuring section 27 and used for measuring the total fluid temperature, the total pressure and the wall static pressure of the engine inlet and used for evaluating the quality of the air inlet flow field of the engine. The simulation bench and the air inlet testing component 2 are used for installing an engine and an air inlet channel thereof, the measuring section of the process air inlet channel can measure all air inlet section airflow parameters through the process air inlet channel rotating component 26, and the operation is convenient and the reliability is high.

As shown in fig. 2, the three-degree-of-freedom lifting platform 3 controls lifting of the platform along a Z direction, rotation along an X axis, and rotation along a Y axis through an actuating system, and is used to simulate a dynamic ground effect of three degrees of freedom of a ship-based test run (the X axis is a horizontal direction of a paper surface, the Y axis is a vertical direction of the paper surface, the Z axis is a vertical direction, in this embodiment, the first direction is the Z direction, the second direction is the Y direction, and the third direction is the X direction). The fourth plane substrate 31 is used for simulating the dynamic ship plane, the fourth plane substrate 31 is provided with a smoke generator 32 and static pressure measuring points 33, the smoke generator 32 is positioned in front of the convergence section 28 of the process air inlet channel and visualizes an engine air inlet flow field by generating smoke, the static pressure measuring points are arranged along the direction of the air inlet channel and are used for measuring the static pressure along the air inlet channel, as shown in figure 5, the fourth plane substrate 31 is fixed on the second hinge support 35, the fourth hinge support 38 and the x-direction servo rolling cylinder 310 through a first hinge support 34, a third hinge support 37 and a fifth hinge support 39, the x-direction servo rolling cylinder 310 is operated through numerical control software and can be operated according to a programmed program, the fourth plane substrate 31 is controlled to rotate along the first hinge support 34 and the third hinge support 37 through the rolling cylinders, rolling control of the fourth plane substrate 31 along the x axis is realized, an x-direction rolling indicating device 311 is arranged below the fourth plane substrate 31, when the fourth plane substrate 31 is arranged on the third hinge support 34 and the third hinge support 37, the rolling cylinder is controlled to rotate along the x-direction through the rolling cylinder 12, the ninth hinge support 316 and the rolling cylinder 316, the rolling indicating device is arranged on the ninth hinge support and the ninth hinge cylinder 316, the ninth hinge 316, the rolling cylinder 316 and the ninth hinge 316, the rolling cylinder 316 can be programmed according to the rolling direction of the rolling cylinder control device for limiting the rolling base 316, the rolling control of the fourth plane base layer 31 and the third plane base layer 36 along the y axis is realized, a y-direction rolling indicating device 317 is installed below the third plane base layer 36, when the third plane base layer 36 rolls to a designed limit position, the y-direction rolling indicating device 317 falls into a y-direction rolling limiting device 318 installed on the second plane base layer 319 to limit the y-direction limit rolling position, the second plane base layer 319 is fixed on the first plane base layer 322 through a first sliding rail 323, a second sliding rail 324, a third sliding rail 325 and a fourth sliding rail 326, the lower surface 327 of the first plane base layer 322 is connected with a z-direction servo lifting actuator cylinder, the z-direction servo lifting actuator cylinder 327 is controlled by numerical control software, the numerical control software can be operated according to a written program, and the lifting of the second plane base layer 319 along the first sliding rail 323, the second sliding rail 324, the third sliding rail 325 and the fourth sliding rail 326 is controlled through telescopic actuators, so that the lifting of the third plane base layer 319, the third plane base layer 36 and the fourth plane base layer 31 along the z direction is realized.

The embodiment of the invention has the following beneficial effects:

the engine installation of different heights and different air inlet distances of the engine is realized, and the thrust measurement of the engine in a steady state and a transition state is realized.

The engine and the air inlet channel thereof are mounted and adjusted, the measuring section of the process air inlet channel passes through the process air inlet channel rotating assembly 26, all air inlet section airflow parameters can be measured, the operation is convenient, and the reliability is high.

The aircraft engine carrier-based test run device rolls along the x direction and the y direction, is high in control precision, simple in structure and strong in operability, and can simulate the dynamic ground effect of the carrier-based test run of the aircraft engine.

The built-in smoke generator 32 visualizes the engine intake flow field by generating smoke.

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

1. The utility model provides an aeroengine carrier-borne test run developments ground effect analog system, includes three degree of freedom lift platform (3), its characterized in that, three degree of freedom lift platform (3) include:

a first planar substrate (322), a second planar substrate (319), a third planar substrate (36), and a fourth planar substrate (31);

the lifting assembly is arranged on the first plane base layer (322), the second plane base layer (319) is fixedly arranged at the upper end of the lifting assembly, and the second plane base layer (319) can lift relative to the first plane base layer (322) along with the lifting assembly along a first direction;

a second direction rotation member disposed above the second planar base layer (319), the third planar base layer (36) being coupled to the second direction rotation member, and the third planar base layer (36) being capable of rotating in a second direction relative to the second planar base layer (319);

third direction rotating assembly sets up in third plane basic unit (36) top, fourth plane basic unit (31) with third direction rotating assembly connects, and fourth plane basic unit (31) can be for third plane basic unit (36) rotation in the third direction, just first direction, second direction with third direction mutually perpendicular.

2. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 1, further comprising a rack mounting component (1), wherein the rack mounting component (1) is a box-shaped structure with an inner cavity, and the three-degree-of-freedom lifting platform (3) is arranged on a lower bottom surface of the rack mounting component (1).

3. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 2, further comprising a simulation bench and an air inlet test assembly (2) arranged on the upper top surface of the bench mounting assembly (1).

4. The aircraft engine carrier-based test run dynamic ground effect simulation system of claim 3, wherein the simulation bench and air intake test assembly (2) comprises:

the simulation engine (25) is fixedly connected with the upper top surface of the rack mounting assembly (1) through an engine moving frame mounting plate;

and one end of the air supply pipe is connected with the simulation engine (25) for air supply, and the other end of the air supply pipe is arranged on the outer side of the top surface of the upper top surface of the rack mounting assembly (1).

5. The aircraft engine carrier-based test run dynamic ground effect simulation system of claim 4, wherein the simulation bench and air intake test assembly (2) further comprises:

the process air inlet channel is connected with one end of the simulation engine (25) and is connected with the upper top surface of the rack mounting assembly (1) through a flow tube mounting plate (24);

the technical air inlet channel rotating assembly (26) is connected with one end of the technical air inlet channel, the other end of the technical air inlet channel rotating assembly (26) is arranged on the outer side of the top surface of the upper surface of the rack mounting assembly (1), and the technical air inlet channel rotating assembly (26) can drive the technical air inlet channel to rotate relative to the simulation engine (25).

6. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 5, wherein a pulsating pressure measuring device (29) and a temperature and pressure measuring device (210) are arranged on the process air inlet.

7. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 3, wherein a plurality of mounting holes are formed in the upper top surface of the rack mounting assembly (1) and are uniformly distributed at intervals in the second direction, and the simulation rack and the air inlet test assembly (2) can be selectively and fixedly connected with one of the mounting holes.

8. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 3, wherein the rack mounting assembly (1) comprises a plurality of stand columns (12) arranged at intervals, and the upper top surface of the rack mounting assembly (1) and the lower bottom surface of the rack mounting assembly (1) are both connected with the stand columns (12).

9. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 8, wherein the upper end and the lower end of each upright column (12) are provided with adjusting holes for adjusting the mounting positions of the upper top surface of the rack mounting assembly (1) and the lower bottom surface of the rack mounting assembly (1).

10. The aircraft engine carrier-based test run dynamic ground effect simulation system according to claim 2, wherein the three-degree-of-freedom lifting platform (3) is provided with a smoke generator (32) and a static pressure measuring point (33).