CN110411704B - Ejector module for intake and exhaust simulation test of low-speed wind tunnel aircraft - Google Patents
Ejector module for intake and exhaust simulation test of low-speed wind tunnel aircraft Download PDFInfo
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- CN110411704B CN110411704B CN201910742383.2A CN201910742383A CN110411704B CN 110411704 B CN110411704 B CN 110411704B CN 201910742383 A CN201910742383 A CN 201910742383A CN 110411704 B CN110411704 B CN 110411704B
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- 238000004088 simulation Methods 0.000 title claims abstract description 17
- 238000003466 welding Methods 0.000 claims description 6
- 238000002347 injection Methods 0.000 abstract description 6
- 239000007924 injection Substances 0.000 abstract description 6
- 230000000694 effects Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000007789 sealing Methods 0.000 description 3
- 239000000306 component Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Abstract
The invention discloses an ejector module for an intake and exhaust simulation test of a low-speed wind tunnel aircraft, which sequentially comprises an outer frame, a middle frame and an inner frame from outside to inside, wherein the outer frame, the middle frame and the inner frame are connected to form a closed cavity, an air inlet is formed in the outer frame and communicated with the closed cavity, a plurality of nozzle rakes are arranged on the inner frame, one end of each nozzle rake is communicated with the closed cavity, and a nozzle is arranged at the other end of each nozzle rake. The ejector is designed into a module of a model structure and is integrated with the model into a whole; the ejector module adopts a discrete multi-nozzle distributed ejection mode, and has a compact structure; the discrete multi-nozzle distributed injection mode greatly increases the mixing degree between high-energy compressed gas and injected low-energy gas, so that the injection efficiency is obviously improved.
Description
Technical Field
The invention relates to the field of wind tunnel tests, in particular to an ejector module for a low-speed wind tunnel aircraft air intake and exhaust simulation test.
Background
In the intake and exhaust simulation test of the low-speed wind tunnel aircraft, the simulation of an aircraft power device is a key technical link; the ejector serves as a core component and is used for simulating the working condition of a power device of an aircraft. The purpose of the low-speed wind tunnel aircraft air intake and exhaust simulation test is to obtain the data of the influence of the air intake effect and the exhaust effect on the aerodynamic force of the aircraft when the aircraft power device works.
In a low-speed wind tunnel, an original injection type simulator (EPES) for carrying out an aircraft air inlet and exhaust simulation test is an independent device and is characterized in that: the EPES is taken as an independent part, adopts a circular seam type peripheral injection mode, has a relatively simple structure and is easy to install in a model; the EPES is required to be completely non-contact with the model during the test, and the pneumatic load of the model can be directly measured by a balance. The disadvantages are that: in the test process, the EPES is difficult to ensure complete non-contact with the model, and the requirements of good sealing and incapability of transmitting external force are met; the flat aircraft model with a plurality of embedded engines is limited by the model space and the layout mode of the power device, so that the requirements are extremely difficult to meet, and the influence data of the clean air intake and exhaust effect on the aerodynamic force of the aircraft are not easy to obtain in the test.
Disclosure of Invention
The invention aims to solve the problems of air inlet and exhaust simulation tests of a flat aircraft with a plurality of embedded power devices, and designs an ejector module for the air inlet and exhaust simulation tests of a low-speed wind tunnel aircraft.
In order to achieve the purpose, the invention adopts the following technical scheme:
the utility model provides an ejector module for low-speed wind tunnel aircraft air inlet and exhaust analogue test, includes frame, center and inside casing from outer to interior in proper order, constitutes an airtight cavity between frame, center and the inside casing interconnect back, be provided with air inlet and airtight cavity intercommunication on the frame, be provided with a plurality of nozzle harrow on the inside casing, the one end and the airtight cavity intercommunication of every nozzle harrow are provided with the nozzle on the other end on the nozzle harrow.
In the technical scheme, the middle frame comprises two separated frames, the two frames are not in contact, the outer sides of the frames are connected with the inner wall of the outer frame, and the inner sides of the frames are connected with the inner frame.
In the above technical solution, the inner wall of the outer frame is provided with a protruding step along the frame surface direction, and both sides of the step are used for respectively arranging a frame.
In the technical scheme, the inner frame structure of the middle frame is a kidney-shaped groove, the inner frame is a kidney-shaped structure, and the kidney-shaped structure of the inner frame is matched with the kidney-shaped groove of the middle frame.
In the technical scheme, a plurality of mounting grooves are uniformly and symmetrically distributed on the frame surface of the inner frame, and a nozzle rake is fixedly connected in each mounting groove.
In the technical scheme, the plurality of nozzle harrows are arranged on the inner frame in the direction perpendicular to the frame surface, and the nozzles on each nozzle harrow are arranged along the same direction.
In the technical scheme, three nozzles are uniformly arranged on each nozzle rake, and the nozzles are communicated with the closed cavity through the nozzle rakes.
In the technical scheme, the opening of the nozzle is in a horn shape, and the nozzle rake are fixed into a whole through welding.
In the technical scheme, the outer frame, the middle frame, the inner frame and the nozzle harrow are connected into a hollow closed integral structure through welding.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the ejector is designed into a module of a model structure and is integrated with the model into a whole; the ejector module adopts a discrete multi-nozzle distributed ejection mode, and has a compact structure;
the ejector module is used as a power device simulator and is driven to work by a high-pressure air source, and the ejector module ejects air flow and jet air flow and simultaneously simulates the air inlet effect and the air exhaust effect of an aircraft power device;
the discrete multi-nozzle distributed injection mode greatly increases the mixing degree between high-energy compressed gas and injected low-energy gas, so that the injection efficiency is obviously improved;
when the wind tunnel air intake and exhaust test is carried out, the pneumatic load of the aircraft and the acting force brought by the operation of the ejector module are simultaneously measured by the balance; the existing test equipment and technology are utilized to effectively strip the acting force brought by the work of the ejector module from the model aerodynamic force, and the influence data of the clean air intake and exhaust effect on the aircraft aerodynamic force are obtained.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic illustration of the location of an ejector module in a mold;
FIG. 2 is an injector assembly view;
FIG. 3 is an exploded view of the eductor;
wherein, 1 is an ejector module, 2 is an air inlet, 3 is an air outlet, 1-1 is an outer frame, 1-2 is a middle frame, 1-3 is an inner frame, 1-4 is a nozzle rake, 4 is a convex step, and 5 is a mounting groove.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
As shown in fig. 1, which is a schematic view of the installation structure of this embodiment, the ejector module of the present invention is installed on a test model, an ejector is used to replace an engine of an aircraft model, and dynamic parameters of a real aircraft are simulated in a wind tunnel, so as to realize the acquisition of test data.
The embodiment consists of four parts: the outer frame, the middle frame, the inner frame and the nozzle harrow (comprising the nozzle) of the ejector. The gas transmission pipeline is arranged on a connector of the outer frame of the ejector and guides an external high-pressure gas source into the ejector. In order to avoid air leakage of the ejector, all the components are welded into a whole and are installed in the middle or on two sides of the flat aircraft model as a complete part. The ejector is connected with the model through screws, the ejector is sealed by a sealing strip to prevent air leakage, and the structure after installation is shown in figure 2.
The specific structure of each part of this embodiment is shown in fig. 3, in which:
the outer frame of the ejector is of a rectangular frame surface structure, the part in the frame surface is hollow and is used for fixedly connecting the middle frame and the inner frame, and in order to provide a flowing space for gas in the ejector in the embodiment, a closed cavity is inevitably needed between the outer frame and the inner frame, so that the air flow can be ejected after entering the closed cavity from the outside.
To achieve this, the middle frame is divided into two frames, which are respectively connected to the inner walls of the frame surfaces of the outer frame without contact therebetween, so that an open space is defined between the space between the two frames and the frame surfaces of the outer frame.
In order to realize reliable connection between the outer frame and the middle frame, a circle of convex steps are arranged on the inner side of the frame surface of the outer frame along the direction of the frame surface, mounting spaces are reserved on two sides of each step, the frame of the middle frame is mounted on two sides of each step, the convex height of each step is consistent with the thickness of the middle frame, after the frame of the middle frame is fixedly connected with the outer frame through welding, the inner wall surface of the frame is completely matched with the convex steps, the condition of unevenness cannot occur, and the stability of an airflow field is ensured.
The inner frame is a waist-shaped frame surface structure formed by winding a complete rectangular surface structure, and specifically, as shown in fig. 3, a plurality of mounting grooves are arranged on the frame surface and arranged along the same direction. In order to ensure the accurate flow of the gas, the mounting groove is positioned between the two frames of the middle frame, and the nozzle harrow can be completely communicated with the closed cavity after the nozzle harrow is mounted in the mounting groove.
In order to realize the ejection of gas from a closed space, nozzles are required to be arranged on the nozzle harrows, three nozzles are arranged on each nozzle harrow, the openings of the nozzles are of a horn-shaped structure, all the nozzles are fixedly welded on the nozzle harrows, the nozzles on each nozzle harrow are uniformly distributed, each nozzle harrow is uniformly distributed on the inner frame, and the nozzles of the whole nozzle harrows are discretely distributed in the ejector.
In the embodiment, the ejector needs to bear the pressure of high-pressure gas, and the ejector is required to have good sealing performance, so that the four components are connected into a whole in a welding mode, a closed cavity is formed among the outer frame, the middle frame, the inner frame and the nozzle rake, and gas can enter the closed cavity from a pipeline connected with an external high-pressure gas source of the ejector outer frame and is sprayed out from a nozzle on the nozzle rake.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (8)
1. The utility model provides an ejector module for low-speed wind tunnel aircraft air inlet and exhaust analogue test, its characterized in that includes frame, center and inside casing in proper order from outer to interior, constitutes a airtight cavity between frame, center and the inside casing interconnect back, be provided with air inlet and airtight cavity intercommunication on the frame, the distribution of even symmetry has a plurality of mounting groove on the frame face of inside casing, nozzle harrow of fixed connection in each mounting groove, and the one end and the airtight cavity intercommunication of every nozzle harrow are provided with the nozzle on the other end on the nozzle harrow.
2. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to claim 1, wherein the middle frame comprises two separated frames, the two frames are not in contact with each other, the outer sides of the frames are connected with the inner wall of the outer frame, and the inner sides of the frames are connected with the inner frame.
3. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to claim 2, wherein the inner wall of the outer frame is provided with a protruding step along the frame surface direction, and two sides of the step are respectively provided with a frame.
4. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to claim 2, wherein the inner frame of the middle frame is a kidney-shaped groove, the inner frame is a kidney-shaped structure, and the kidney-shaped structure of the inner frame is matched with the kidney-shaped groove of the middle frame.
5. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to claim 1, wherein the plurality of nozzle rakes are arranged on the inner frame in a direction perpendicular to the frame surface, and the nozzles on each nozzle rake are arranged along the same direction.
6. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to claim 1, wherein three nozzles are uniformly arranged on each nozzle rake, and the nozzles are communicated with the closed cavity through the nozzle rakes.
7. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to claim 5 or 6, wherein the opening of the nozzle is horn-shaped, and the nozzle rake are fixed into a whole by welding.
8. The ejector module for the intake and exhaust simulation test of the low-speed wind tunnel aircraft according to any one of claims 1 to 4, wherein the outer frame, the middle frame, the inner frame and the nozzle rake are connected by welding to form a hollow closed integral structure.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910742383.2A CN110411704B (en) | 2019-08-13 | 2019-08-13 | Ejector module for intake and exhaust simulation test of low-speed wind tunnel aircraft |
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| CN201910742383.2A CN110411704B (en) | 2019-08-13 | 2019-08-13 | Ejector module for intake and exhaust simulation test of low-speed wind tunnel aircraft |
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| CN110411704A CN110411704A (en) | 2019-11-05 |
| CN110411704B true CN110411704B (en) | 2020-11-06 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114932019B (en) * | 2022-07-25 | 2022-11-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for controlling expansion angle of rectangular jet flow |
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| JPH0843248A (en) * | 1994-07-28 | 1996-02-16 | Hitachi Ltd | Supersonic wind tunnel |
| RU2312320C2 (en) * | 2005-07-28 | 2007-12-10 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Device for testing the objects of aeronautical engineering working under icing conditions |
| CN101097167A (en) * | 2005-12-30 | 2008-01-02 | 大连理工大学 | Multifunctional gas wave refrigerating jet stream field displaying apparatus and method for measuring |
| CN105738068A (en) * | 2016-01-28 | 2016-07-06 | 南京航空航天大学 | Device used for reducing profile rotation continuously adjustable wind tunnel nozzle adjusting actuating force |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL92675C (en) * | 1954-04-27 | |||
| JPH02500999A (en) * | 1986-08-07 | 1990-04-05 | イギリス国 | Test equipment and method |
| JPS6342440A (en) * | 1986-08-08 | 1988-02-23 | Tokyo Electron Ltd | Visualizing method for gas flow in airtight container |
| CN103616155B (en) * | 2013-11-29 | 2016-02-17 | 中国人民解放军国防科学技术大学 | The flow control apparatus of supersonic flow field |
| CN107436219B (en) * | 2017-08-02 | 2023-05-26 | 中国航空工业集团公司哈尔滨空气动力研究所 | Inlet and exhaust pipeline device in unconventional layout form |
| CN108194204B (en) * | 2017-12-28 | 2020-03-03 | 西安航天动力研究所 | High-reliability integral injector |
| CN108844708B (en) * | 2018-09-11 | 2020-03-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Injection type nacelle sonic nozzle combination arrangement method |
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2019
- 2019-08-13 CN CN201910742383.2A patent/CN110411704B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0843248A (en) * | 1994-07-28 | 1996-02-16 | Hitachi Ltd | Supersonic wind tunnel |
| RU2312320C2 (en) * | 2005-07-28 | 2007-12-10 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Device for testing the objects of aeronautical engineering working under icing conditions |
| CN101097167A (en) * | 2005-12-30 | 2008-01-02 | 大连理工大学 | Multifunctional gas wave refrigerating jet stream field displaying apparatus and method for measuring |
| CN105738068A (en) * | 2016-01-28 | 2016-07-06 | 南京航空航天大学 | Device used for reducing profile rotation continuously adjustable wind tunnel nozzle adjusting actuating force |
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| CN110411704A (en) | 2019-11-05 |
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