CN214149838U - Comprehensive test bed for turbojet engine and vectoring nozzle - Google Patents
Comprehensive test bed for turbojet engine and vectoring nozzle Download PDFInfo
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- CN214149838U CN214149838U CN202120395323.0U CN202120395323U CN214149838U CN 214149838 U CN214149838 U CN 214149838U CN 202120395323 U CN202120395323 U CN 202120395323U CN 214149838 U CN214149838 U CN 214149838U
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Abstract
The utility model discloses a comprehensive test bed of a turbojet engine and a vectoring nozzle, which comprises a horizontally placed test bed base (4), a horizontal stop block (41) is arranged on the upper part of one end of the test bed base (4), a horizontal sliding table (42) is arranged on the test bed base (4), the turbojet engine (1) is horizontally arranged on the horizontal sliding table (42) and can slide to a certain position along the length direction of the horizontal sliding table for locking, a pressure sensor (43) is arranged between the horizontal stop block (41) and the horizontal sliding table (42), the pressure sensor is arranged on the test bed base (4) and below the air inlet of the turbojet engine (1), the vector spray pipe (2) is horizontally arranged at the spray port of the turbojet engine (1), is connected to the vectoring nozzle (2) through a transverse sensor (45) arranged on the upright post (44), a longitudinal sensor (46) is also connected to the vectoring nozzle (2) below the outlet.
Description
The technical field is as follows:
the utility model relates to an aeronautical test field, concretely relates to turbojet engine and vectoring nozzle's integrated test platform.
Background art:
at present, in the development and manufacturing process of fighters, the pneumatic and power verification of a scaling aircraft engineering prototype manufactured in advance is an indispensable test step. The realization of related functions of vertical take-off and landing, catapult take-off, high maneuvering flight and the like of the advanced fighter plane can not leave the guarantee of the thrust vectoring nozzle of the turbojet engine. However, at the stage of a scaled fighter model, a ground experimental means and a ground experimental method for the thrust comprehensive characteristics of a turbojet engine and a vectoring nozzle are lacked.
However, most of power devices assembled by the fighter scaled model in the prior art are civil small turbojet engines, related testing means are that a simple support or a rack cannot test the force and moment characteristics related to an engine vector nozzle, and a small turbojet engine test rack mainly tests performance parameters of the engine, is not combined with the vector nozzle, and cannot be used for power system verification of the fighter scaled model.
In addition, in the invention patent of patent publication No. CN108225776A, the nozzle and the engine are mounted on the sensor as a whole, and since the moment in the three-dimensional direction (front-back, left-right, up-down) of the vectoring nozzle is to be tested, the vectoring nozzle must be mounted on a six-component balance or other device capable of testing the forces in all directions, but when the test is performed in this way, the center of gravity of the system is high, the safety cannot be guaranteed, the collected data cannot be directly used for power system verification and structural analysis, and the vectoring thrust needs to be converted into the force acting on the mounting point through the moment, which causes errors.
Therefore, in order to verify the thrust and the pneumatic performance of the vertical take-off and landing and the catapult take-off and landing fighters, a novel small turbojet engine and a vectoring nozzle measuring system thereof need to be designed for carrying out a preliminary ground test.
The utility model has the following contents:
to the not enough among the above-mentioned prior art, the utility model provides a turbojet engine and vectoring nozzle's integrated test platform has realized under safe and low-cost prerequisite, directly measuring turbojet engine and vectoring nozzle's thrust and the vector force moment that acts on the vectoring nozzle mounting point, provides ground verification means for the advanced fighter research and development of installing the vectoring nozzle additional.
In order to achieve the above purpose, the technical solution of the present invention is as follows: the utility model provides a turbojet engine and vectoring nozzle's integrated test platform, including the test bench base that a level was placed, place horizontal dog on the upper portion of test bench base one end, horizontal slip table sets up on the test bench base, turbojet engine horizontal installation is on horizontal slip table, and can slide to a certain position locking along horizontal slip table's length direction, install a pressure sensor between horizontal dog and horizontal slip table, pressure sensor establishes on the test bench base and in the below of turbojet engine air inlet, turbojet engine's jet outlet horizontal installation vectoring nozzle, connect on vectoring nozzle through the horizontal sensor who installs on the stand, still connect a longitudinal sensor in vectoring nozzle's below that is close to the export.
In one embodiment, a fastening device is further mounted on the turbojet engine, the turbojet engine is fastened on the horizontal sliding table through the fastening device, and the fastening device can be adjusted according to the size and the shape of the turbojet engine.
In one embodiment, a T-shaped groove is formed on the horizontal sliding table.
In one embodiment, a vectoring nozzle is further mounted at the outlet end of the vectoring nozzle, and gas ejected during the operation of the turbojet is discharged through the vectoring nozzle and the vectoring nozzle, the direction and the opening size of which can be controlled by an aircraft control system, so that thrust acting on the aircraft fuselage is generated.
In one embodiment, the pressure sensor is connected to a digital display screen or a computer.
In one embodiment, the upright is mounted on the test bed base and is adjustable according to the mounting position of the vectoring nozzle.
In one embodiment, a bolt is further arranged below the jet port of the turbojet engine and on the horizontal sliding table, and the inlet end of the vectoring nozzle is connected to the bolt.
In one embodiment, the height of the horizontal stop is in the range of 3-10 cm.
The utility model discloses a main innovation point or beneficial effect lie in:
first, pressure sensor's the general way of arranging the position is arranged at engine rear exhaust position (i.e. the right side of the turbojet engine in fig. 1) at prior art's general practice, and the use is tension sensor, the utility model discloses change general sensor type, become the pressure formula with the sensor of thrust test by the pulling force formula, arrange in the department of admitting air, vacate the exhaust position and supply vector spray pipe installation and test.
Secondly, the height range of the horizontal stop block is set to be 3-10cm, which cannot be too low or cannot provide support for the pressure sensor, and also cannot be too high, which can affect the air intake of the engine, and the test result is inaccurate.
And thirdly, the horizontal sliding table is provided with a T-shaped groove and a movable fastening device, so that the comprehensive test bed can adapt to engines with different sizes and shapes, and has universality.
Fourthly, the vectoring nozzle is connected to a mounting point designed by the nozzle through a longitudinal mechanical sensor and a transverse sensor arranged on a stand column, the measured value of the mechanical sensor is the force value of the system acting on the fuselage on the airplane, and the test bed can directly obtain the vectoring thrust value of each angle and is directly used for strength analysis of the fuselage structural part and the fastening part;
fifthly, the position of the upright post can be adjusted through a T-shaped groove and a fastening bolt on the base of the test bed so as to adapt to the installation of vector spray pipes of different models, and the comprehensive test bed has universality.
Sixthly, the whole equipment is horizontally integrated on the test bed base, the gravity center is very low, the engine test of new performance is safer, devices such as thermocouples, flow velocity sensors and the like can be conveniently additionally arranged, and the temperature distribution, the exhaust speed and other data of the turbojet engine and the vector spray pipe can be tested simultaneously under the condition that the thrust vector data test result is not influenced.
To sum up, the utility model provides a turbojet engine and vectoring nozzle's integrated test platform has realized under safety and low-cost prerequisite, directly measuring turbojet engine and vectoring nozzle's thrust and the vector force moment that acts on the vectoring nozzle mounting point, provides ground verification means for the advanced fighter research and development of installing the vectoring nozzle additional.
Description of the drawings:
the above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which like reference numerals refer to like features throughout, and in which:
fig. 1 shows an installation layout of a combined test stand for a turbojet and a vectoring nozzle according to an embodiment of the present invention.
In the illustration:
4-a base of the test bed,
41-a horizontal stop block, wherein the horizontal stop block is arranged on the horizontal stop block,
42-a horizontal sliding table is arranged on the upper portion of the sliding table,
1-a turbojet engine, a jet engine,
43-a pressure sensor, the pressure sensor,
44-the vertical column is arranged on the upper portion of the frame,
45-the lateral direction sensor or sensors,
2-a vector spray pipe is arranged in the nozzle,
46-a longitudinal sensor-the longitudinal direction of the sensor,
422-a fastening device for the fastening device,
421-bolt.
The specific implementation mode is as follows:
the present invention will be described in detail with reference to the following embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not limited thereto, and all modifications or equivalent substitutions made to the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention should be covered in the protection scope of the present invention. It should be noted that the relationships depicted in the figures are for illustrative purposes only and are not to be construed as limiting the patent.
Referring to FIG. 1, FIG. 1 illustrates an exemplary embodiment of a test rig for a turbojet engine and a vectoring nozzle. In this embodiment, the integrated test bed for the turbojet engine and the vectoring nozzle comprises a horizontally arranged test bed base 4, a horizontal stop block 41 is arranged on the upper portion of one end of the test bed base 4, a horizontal sliding table 42 is arranged on the test bed base 4, the turbojet engine 1 is horizontally arranged on the horizontal sliding table 42 and can slide to a certain position along the length direction of the horizontal sliding table to be locked, a pressure sensor 43 is arranged between the horizontal stop block 41 and the horizontal sliding table 42, the pressure sensor 43 is arranged on the test bed base 4 and below an air inlet of the turbojet engine 1, the vectoring nozzle 2 is horizontally arranged at a spraying port of the turbojet engine 1, the vectoring nozzle 2 is connected to the vectoring nozzle 2 through a transverse sensor 45 arranged on a stand column 44, and a longitudinal sensor 46 is further connected below the vectoring nozzle 2 close to the outlet.
Further, a fastening device 422 is further installed on the turbojet engine 1, the turbojet engine 1 is fastened to the horizontal sliding table 42 through the fastening device 422, and the fastening device 422 can be adjusted according to the size and the shape of the turbojet engine 1.
Further, a T-shaped groove is formed on the horizontal sliding table 42.
Furthermore, a vector nozzle 3 is arranged at the outlet end of the vector nozzle 2, and gas sprayed during the operation of the turbojet engine 1 is discharged through the vector nozzle 2 and the vector nozzle 3 with the direction and the opening size controllable by an aircraft control system to generate thrust acting on an aircraft fuselage.
Further, the pressure sensor 43 is connected to a digital display screen or a computer, and records the thrust generated by the turbojet engine in real time.
Further, the upright column 44 is installed on the test bed base 4 and can be adjusted according to the installation position of the vectoring nozzle 2.
Further, a bolt 421 is provided below the discharge port of the turbojet engine 1 and on the horizontal sliding table 42, and the inlet end of the vectoring nozzle 2 is connected to the bolt 421.
Further, the height of the horizontal block 41 ranges from 3 cm to 10 cm.
It should be noted that the prior art in the protection scope of the present invention is not limited to the embodiments given in the present application, and all the prior art which is not contradictory to the solution of the present invention, including but not limited to the prior patent documents, the prior publications, and the like, can be incorporated into the protection scope of the present invention. In addition, the combination of the features in the present application is not limited to the combination described in the claims of the present application or the combination described in the embodiments, and all the features described in the present application may be freely combined or combined in any manner unless contradictory to each other. It should also be noted that the above-mentioned embodiments are only specific embodiments of the present invention. It is obvious that the present invention is not limited to the above embodiments, and similar changes or modifications can be directly derived or easily suggested by those skilled in the art from the disclosure of the present invention, and all should fall within the protection scope of the present invention.
Claims (8)
1. The utility model provides a comprehensive test platform of turbojet engine and thrust vectoring nozzle which characterized in that: including test bench base (4) that a level was placed, place horizontal dog (41) on the upper portion of test bench base (4) one end, horizontal slip table (42) set up on test bench base (4), turbojet engine (1) horizontal installation is on horizontal slip table (42), and can slide to a certain position locking along the length direction of horizontal slip table, install a pressure sensor (43) between horizontal dog (41) and horizontal slip table (42), pressure sensor establishes on test bench base (4) and in the below of turbojet engine (1) air inlet, the jet orifice horizontal installation vector spray tube (2) of turbojet engine (1), connect on vector spray tube (2) through horizontal sensor (45) of installing on stand (44), still connect a longitudinal sensor (46) in vector spray tube (2) below that is close to the export.
2. The integrated test stand of claim 1, wherein: and a fastening device (422) is further installed on the turbojet engine (1), the turbojet engine (1) is fastened on the horizontal sliding table (42) through the fastening device (422), and the fastening device (422) can be adjusted according to the size and the shape of the turbojet engine (1).
3. The integrated test stand of claim 1, wherein: and a T-shaped groove is formed on the horizontal sliding table (42).
4. The integrated test stand of claim 1, wherein: and a vectoring nozzle (3) is further installed at the outlet end of the vectoring nozzle (2), and gas sprayed during the operation of the turbojet engine (1) is discharged through the vectoring nozzle (2) and the vectoring nozzle (3) with the direction and the opening size controllable by an aircraft control system to generate thrust acting on an aircraft fuselage.
5. The integrated test stand of claim 1, wherein: the pressure sensor (43) is connected with a digital display screen or a computer.
6. The integrated test stand of claim 1, wherein: the upright post (44) is arranged on the test bed base (4) and can be adjusted according to the installation position of the vectoring nozzle (2).
7. The integrated test stand of claim 3, wherein: and a bolt (421) is further arranged below a spraying port of the turbojet engine (1) and on the horizontal sliding table (42), and the inlet end of the vectoring nozzle (2) is connected to the bolt (421).
8. The integrated test stand of claim 1, wherein: the height range of the horizontal stop block (41) is 3-10 cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202120395323.0U CN214149838U (en) | 2021-02-23 | 2021-02-23 | Comprehensive test bed for turbojet engine and vectoring nozzle |
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| CN202120395323.0U CN214149838U (en) | 2021-02-23 | 2021-02-23 | Comprehensive test bed for turbojet engine and vectoring nozzle |
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| CN214149838U true CN214149838U (en) | 2021-09-07 |
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| CN113945386A (en) * | 2021-09-19 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining thrust of ground tackle dynamic test engine of power transmission and emission system |
| CN113945387A (en) * | 2021-09-19 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Ground pulley test method for forward-launch-emission system |
| CN113959726A (en) * | 2021-09-21 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Power system of jet engine ground test platform |
| CN114235426A (en) * | 2021-12-16 | 2022-03-25 | 南京航空航天大学 | Support miniature turbojet engine test bench of dysmorphism spray tube |
| CN114813155A (en) * | 2022-06-27 | 2022-07-29 | 中国航发四川燃气涡轮研究院 | Engine exhaust vector angle measurement and tail flame monitoring system |
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2021
- 2021-02-23 CN CN202120395323.0U patent/CN214149838U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113945386A (en) * | 2021-09-19 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining thrust of ground tackle dynamic test engine of power transmission and emission system |
| CN113945387A (en) * | 2021-09-19 | 2022-01-18 | 中国航空工业集团公司西安飞机设计研究所 | Ground pulley test method for forward-launch-emission system |
| CN113945386B (en) * | 2021-09-19 | 2023-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Thrust determination method for ground pulley dynamic test engine of hair extension system |
| CN113945387B (en) * | 2021-09-19 | 2023-11-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground pulley test method for hair extension system |
| CN113959726A (en) * | 2021-09-21 | 2022-01-21 | 中国航空工业集团公司西安飞机设计研究所 | Power system of jet engine ground test platform |
| CN113959726B (en) * | 2021-09-21 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Power system of jet engine ground test platform |
| CN114235426A (en) * | 2021-12-16 | 2022-03-25 | 南京航空航天大学 | Support miniature turbojet engine test bench of dysmorphism spray tube |
| CN114813155A (en) * | 2022-06-27 | 2022-07-29 | 中国航发四川燃气涡轮研究院 | Engine exhaust vector angle measurement and tail flame monitoring system |
| CN114813155B (en) * | 2022-06-27 | 2022-10-25 | 中国航发四川燃气涡轮研究院 | Engine exhaust vector angle measurement and tail flame monitoring system |
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