CN117073969A - Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe - Google Patents
Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe Download PDFInfo
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- CN117073969A CN117073969A CN202311314624.6A CN202311314624A CN117073969A CN 117073969 A CN117073969 A CN 117073969A CN 202311314624 A CN202311314624 A CN 202311314624A CN 117073969 A CN117073969 A CN 117073969A
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- 230000003068 static effect Effects 0.000 title claims abstract description 30
- 238000005259 measurement Methods 0.000 title claims abstract description 29
- 238000002347 injection Methods 0.000 title claims abstract description 25
- 239000007924 injection Substances 0.000 title claims abstract description 25
- 238000000691 measurement method Methods 0.000 title abstract description 4
- 239000002243 precursor Substances 0.000 claims abstract description 20
- 238000009423 ventilation Methods 0.000 claims abstract description 12
- 239000007921 spray Substances 0.000 claims abstract description 10
- 238000000034 method Methods 0.000 claims abstract description 8
- 238000007789 sealing Methods 0.000 claims description 12
- -1 polytetrafluoroethylene Polymers 0.000 claims description 4
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 4
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 4
- 238000012360 testing method Methods 0.000 abstract description 18
- 239000011148 porous material Substances 0.000 description 5
- 238000009530 blood pressure measurement Methods 0.000 description 4
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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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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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
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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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- 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
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Abstract
An accurate measurement device and a measurement method for static thrust of a radial disturbance injection jet pipe belong to the technical field of aeroengine wind tunnel tests. The application solves the problem that the existing jet nozzle measuring device is not suitable for measuring the jet nozzle in a wind tunnel test. The front ends of a main flow pipeline, a secondary flow pipeline and a non-force-measuring precursor are all connected with a double-duct ventilation support, the main flow pipeline is connected with a secondary flow pipeline and a main flow corrugated pipe, the main flow pipeline is connected with a rectifying cone, the secondary flow pipeline is connected with a secondary flow corrugated pipe, the secondary flow corrugated pipe is respectively connected with the main flow corrugated pipe, a ring-type six-component antenna and a force-measuring rear body injection spray pipe, a main flow rectifying device and a secondary flow rectifying device are arranged at the rear end of a rectifying cone, and a main flow pressure measuring rake and a secondary flow pressure measuring rake are arranged at the rear end of the secondary flow rectifying device. The device and the method for accurately measuring the static thrust of the jet nozzle in the radial disturbance can meet the requirement of accurately measuring the static thrust of the jet nozzle in the wind tunnel test process of the jet nozzle.
Description
Technical Field
The application belongs to the technical field of aeroengine wind tunnel tests, and particularly relates to a device and a method for accurately measuring static thrust of a radial interference jet nozzle.
Background
The injection nozzle is formed by adding a fixed or adjustable injection sleeve to the main nozzle of the engine. When the jet pipe works, viscous mixing action of the high-energy main flow jet sucks secondary flow, so that the secondary flow flows between the main flow column and the jet sleeve, the secondary flow restrains expansion of the main flow, the main flow can reach or nearly completely expand by changing the flow direction of the secondary flow, and the distribution structure of impulse can be changed by exchanging the main flow and the secondary flow, so that the thrust is increased. In addition, the jet nozzle has the advantages of cooling, infrared suppression and the like, is beneficial to simple and compact structure, has good adjusting capability under a large drop pressure ratio, and is widely applied to various aircrafts.
The jet nozzle shrinkage test comprises a static test and a wind tunnel test, the static test technology of the jet nozzle in China is mature at present, but the technology is not popularized to the high-speed wind tunnel test, for example, the application patent with the publication number of CN115931283A discloses a double-duct pipe thrust characteristic accurate measurement device which is mainly applied to static thrust measurement of the jet nozzle, and the device is not applicable to the jet nozzle wind tunnel test because of compact size of a high-speed wind tunnel test model.
Therefore, the application provides the accurate measurement device for the static thrust of the jet nozzle, which has a compact structure, realizes the synchronous and accurate measurement of the thrust of the jet nozzle and the resistance of the outer cover, and develops the research of the wind tunnel test of the thrust and drag reduction characteristics of the jet nozzle.
Disclosure of Invention
The application aims to solve the problem that the existing jet nozzle measuring device is not suitable for measuring the jet nozzle in a wind tunnel test. The following presents a simplified summary of the application in order to provide a basic understanding of some aspects of the application. It should be understood that this summary is not an exhaustive overview of the application. It is not intended to identify key or critical elements of the application or to delineate the scope of the application.
The technical scheme of the application is as follows:
scheme one: the utility model provides a radial disturbance's jet nozzle static thrust accurate measurement device, including the main stream pipeline, the secondary stream pipeline, the non-dynamometry precursor, annular six-component balance, the secondary stream bellows, the main stream bellows, the rectification awl, the main stream fairing, the secondary stream fairing, the main stream pressure measurement harrow, secondary stream pressure measurement harrow and dynamometry rear body jet nozzle, the front end of main stream pipeline, secondary stream pipeline and non-dynamometry precursor all is connected with two duct ventilation support establishment, non-dynamometry precursor is connected with dynamometry rear body jet nozzle, main stream pipeline, secondary stream pipeline and non-dynamometry precursor are arranged in proper order from inside to outside, main stream pipeline is connected with secondary stream pipeline and main stream bellows establishment, the main stream pipeline is connected with the rectification awl establishment through main stream bellows, the secondary stream bellows is connected with main stream bellows, annular six-component level and dynamometry rear body jet nozzle establishment respectively, main stream fairing's rear end has arranged main stream fairing and secondary stream fairing's rear end in proper order, pressure measurement harrow and secondary stream pressure measurement.
Furthermore, a sealing ring is arranged between the non-force-measuring precursor and the force-measuring rear body injection nozzle, and the sealing ring is a ring-type polytetrafluoroethylene sealing ring.
Further, the central axis of the ring-type six-component balance is collinear with the central axis of the main flow pipeline, the central axes of the secondary flow corrugated pipe and the main flow corrugated pipe are parallel, and the central axes of the secondary flow corrugated pipe and the main flow corrugated pipe are respectively perpendicular to the central axis of the main flow pipeline.
Further, the pressure measuring holes of the main flow pressure measuring harrow are distributed in an equal area, the number of the secondary flow pressure measuring harrows is six, and the six secondary flow pressure measuring harrows are distributed at equal intervals along the circumferential direction of the force measuring rear body injection spray pipe.
Further, the distance between the main flow pressure measuring rake and the outlet of the main flow rectifying device is greater than 1.5D, wherein D is the diameter of the main flow rectifying device.
Scheme II: the method is realized by means of the radial disturbance injection jet pipe static thrust accurate measurement device according to the scheme one, and comprises the following two paths:
main flow compressed air path: the main flow compressed air enters a main flow pipeline through an external double-duct ventilation support, enters a main flow corrugated pipe which is radially arranged at the rear end of the main flow pipeline, flows to a main flow pressure measuring rake after being turned by an airflow through a rectifying cone and a main flow rectifying device, and is finally discharged by a main convergence pipe of a force measuring rear body injection spray pipe;
secondary flow compressed air path: the secondary flow compressed air enters the secondary flow pipeline through an external double-duct ventilation support, enters a secondary flow corrugated pipe which is radially arranged at the rear end of the secondary flow pipeline, and reaches a secondary flow pressure measuring rake through a secondary flow rectifying device after air flow turns, and secondary flow air is discharged from an outer jet pipe of the force measuring rear body jet pipe.
The application has the following beneficial effects:
1. the accurate measurement device for the static thrust of the jet nozzle with radial disturbance can meet the high-pressure air supply requirement of double ducts in the wind tunnel test of the jet nozzle, reduce the influence of the pressure, momentum and the like of the high-pressure air on balance measurement, and realize the accurate measurement of the static thrust of the jet nozzle;
2. the accurate measuring device for the static thrust of the jet nozzle with radial disturbance has a simple and compact structure, and is suitable for a high-speed wind tunnel test model with a narrow interior;
3. the application relates to a static thrust accurate measurement device of a radial disturbance injection jet pipe, which is provided with two sets of main flow corrugated pipes and two sets of secondary flow corrugated pipes, wherein the two sets of main flow corrugated pipes and the two sets of secondary flow corrugated pipes are arranged in mirror symmetry by taking an XZ plane as a reference and are perpendicular to the central axis of a main flow pipeline, and the flow impulse effect in a high-pressure pipeline is eliminated in the radial direction, so that the measurement of a balance is not influenced;
4. the interference quantity of the main flow pipeline and the secondary flow pipeline of the radial interference-free jet pipe static thrust accurate measurement device is decoupled from each other, can be used in combination under different pressures, is easy to correct test data, fills up gaps between a non-force-measuring precursor and a force-measuring post-body jet pipe by adopting a ring-type polytetrafluoroethylene sealing ring, plays a sealing role when pressure difference exists between the inside and the outside of a model, and does not want balance measurement end force transmission;
5. the double-channel corrugated pipe of the radial disturbance injection jet pipe static thrust accurate measurement device adopts a radial arrangement structure, and can simultaneously meet the high-pressure air supply requirement that the core main flow and the annular secondary flow of the double-channel test piece are respectively and independently controlled and measured.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a precise measurement device for the static thrust of a jet nozzle with radial disturbance;
fig. 2 is a schematic diagram of a rectifying orifice plate of a main flow rectifying device in a triangular layout.
In the figure: the device comprises a main flow pipeline 1, a secondary flow pipeline 2, a 3-non-force-measuring precursor, a 4-ring six-component balance, a 5-sealing ring, a 6-secondary flow corrugated pipe, a 7-main flow corrugated pipe, an 8-rectifying cone, a 9-main flow rectifying device, a 10-secondary flow rectifying device, a 11-main flow pressure measuring rake, a 12-secondary flow pressure measuring rake and a 13-force-measuring rear body injection spray pipe.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, the present application is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the application. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present application.
The connection mentioned in the present application is divided into a fixed connection and a detachable connection, wherein the fixed connection (i.e. the non-detachable connection) includes, but is not limited to, a conventional fixed connection manner such as a hemmed connection, a rivet connection, an adhesive connection, a welded connection, etc., and the detachable connection includes, but is not limited to, a conventional detachable manner such as a threaded connection, a snap connection, a pin connection, a hinge connection, etc., and when the specific connection manner is not specifically limited, at least one connection manner can be found in the existing connection manner by default, so that the function can be realized, and a person skilled in the art can select the connection according to needs. For example: the fixed connection is welded connection, and the detachable connection is hinged connection.
In the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
In embodiment 1, referring to fig. 1, an ejector nozzle static thrust accurate measurement device for radial disturbance in this embodiment is described, including a main flow pipeline 1, a secondary flow pipeline 2, a non-force-measuring precursor 3, a ring-type six-component balance 4, a secondary flow bellows 6, a main flow bellows 7, a rectifying cone 8, a main flow rectifying device 9, a secondary flow rectifying device 10, a main flow pressure measuring rake 11, a secondary flow pressure measuring rake 12 and a force-measuring rear body ejector nozzle 13, wherein front ends of the main flow pipeline 1, the secondary flow pipeline 2 and the non-force-measuring precursor 3 are all connected with a double-duct ventilation support, the non-force-measuring precursor 3 is connected with the force-measuring rear body ejector nozzle 13, the main flow pipeline 1, the secondary flow pipeline 2 and the non-force-measuring precursor 3 are sequentially arranged from inside to outside, the main flow pipeline 1 is connected with the secondary flow pipeline 2 and the main flow bellows 7, the main flow bellows 1 is connected with the rectifying cone 8, the secondary flow pipeline 2 is connected with the secondary flow bellows 6, the secondary flow bellows 6 is respectively connected with the main flow bellows 7, the ring-type six-component 4 and the ejector nozzle 13, the rear body ejector nozzle 13 is sequentially arranged at the rear end of the rectifying device 10 and the rectifying device 10 is sequentially arranged at the rear end of the rectifying device 10.
The double-duct ventilation support arranged outside is a fixed part of the measuring device, the front ends of the main flow pipeline 1, the secondary flow pipeline 2 and the non-force-measuring precursor 3 are fixedly connected with the double-duct ventilation support outside, the rear end of the main flow pipeline 1 is connected with the rear end of the secondary flow pipeline 2, the rear end of the main flow pipeline 1 is also connected with the front end of the main flow corrugated pipe 7, the main flow corrugated pipe 7 is connected with the rectifying cone 8, the rear end of the rectifying cone 8 is sequentially provided with a main flow rectifying device 9, a secondary flow rectifying device 10 and a main flow pressure measuring rake 11, and six secondary flow pressure measuring rakes 12 are uniformly arranged on the outer circumference of the main flow pressure measuring rake 11; the rear end of the secondary flow pipeline 2 is connected with the front end of the secondary flow corrugated pipe 6, the rear end of the secondary flow corrugated pipe 6 is respectively connected with the rear end of the main flow corrugated pipe 7, the two side ends of the ring-type six-component balance 4 and the force-measuring rear body injection spray pipe 13, the distance between the main flow pressure measuring rake 11 and the outlet of the main flow rectifying device 9 is greater than 1.5D, wherein D is the diameter of the main flow rectifying device 9, so that main flow is fully and uniformly mixed after passing through the main flow rectifying device 9, and the measuring accuracy of the main flow pressure measuring rake 11 is ensured.
When no load and high pressure air exist, the central axis of the ring-type six-component balance 4 is collinear with the central axis of the main flow pipeline 1, and the central axis of the main flow corrugated pipe 7 and the central axis of the secondary flow corrugated pipe 6 are parallel and perpendicular to the central axis of the main flow pipeline 1.
When no load exists, high-pressure gas exists, but the high-pressure gas does not flow, the internal pressures of the main flow corrugated pipe 7 and the secondary flow corrugated pipe 6 are equal and self-counteracted on the premise of symmetrical processing and installation, and the influence on a balance can be eliminated.
When no load exists, high-pressure gas exists, and the high-pressure gas flows, on the premise of symmetrical processing and installation, the impulses of the gas flowing out of the two sets of main flow corrugated pipes 7 are equal and opposite, the impulses are mutually counteracted, the influence of the impulses on the ring-type six-component balance 4 can be eliminated, and the secondary flow corrugated pipes 6 are identical.
A gap is reserved between the non-force-measuring precursor 3 and the force-measuring rear body injection nozzle 13, the ring-type six-component balance 4 only measures the rear outer cover resistance and the nozzle thrust of the force-measuring rear body injection nozzle 13, the resultant force is the static thrust of the nozzle, the ring-type six-component balance 4 does not measure the aerodynamic force of the non-force-measuring precursor 3, in the test, the inner cavity of the model is sealed with the environment through the sealing ring 5 due to the pressure difference between the inside and the outside of the model, the force is not transmitted to the measuring end of the balance, and the sealing ring 5 is a ring-type polytetrafluoroethylene sealing ring.
The main flow rectifying device 9 comprises a rectifying pore plate and a honeycomb device, wherein the open pore form on the rectifying pore plate is in triangular distribution, the triangle formed by connecting the centers of any three holes is in an equilateral triangle, as shown in fig. 2, the rectifying pore plate is relatively in radial distribution, the radial pressure of compressed gas is respectively smaller in difference after passing through the rectifying pore plate in the triangular distribution, the overall uniformity is more excellent, and the better rectifying effect can be achieved after the secondary vortex breaking and blending are carried out by matching with the honeycomb device.
The pressure measuring holes of the main flow pressure measuring harrow 11 are distributed in an equal area mode, so that the pressure uniformity of the measured section can be reflected more accurately, the total number of the secondary flow pressure measuring harrows 12 is six, and the secondary flow pressure measuring harrows are distributed at equal intervals along the circumferential direction of the force measuring rear body injection jet pipe 13.
Embodiment 2, referring to fig. 1, illustrates a method for accurately measuring static thrust of a jet nozzle in radial disturbance according to the embodiment, where the method includes the following two paths:
main flow compressed air path: the main flow compressed air enters the main flow pipeline 1 through an external double-duct ventilation support, enters a main flow corrugated pipe 7 which is radially arranged at the rear end of the main flow pipeline 1, flows to a main flow pressure measuring rake 11 after being turned by an airflow through a rectifying cone 8 and a main flow rectifying device 9, and is finally discharged by a main convergence pipe of a force measuring rear body injection jet pipe 13;
secondary flow compressed air path: the secondary flow compressed air enters the secondary flow pipeline 2 through an external double-duct ventilation support, enters a secondary flow corrugated pipe 6 which is radially arranged at the rear end of the secondary flow pipeline 2, and reaches a secondary flow pressure measuring rake 12 through a secondary flow rectifying device 10 after the air flow turns, and the secondary flow air flow is discharged from an external jet pipe of a force measuring rear body jet pipe 13;
the accurate measurement method of the static thrust of the jet nozzle 13 comprises the following steps: the outer cover resistance and the jet thrust of the jet nozzle 13 are connected to the measuring end of the ring-type six-component balance 4, and meanwhile, in order to supply high-pressure compressed air to the jet nozzle 13, the front end of the jet nozzle 13 is also connected with the main flow pipeline 1 and the secondary flow pipeline 2, and the outer cover resistance and the jet thrust of the jet nozzle 13 are simultaneously transmitted to the ring-type six-component balance 4, the main flow pipeline 1 and the secondary flow pipeline 2. The rigidity of the air supply pipeline is reduced by radially arranging a secondary flow corrugated pipe 6 and a primary flow corrugated pipe 7 between the primary flow pipeline 1 and the secondary flow pipeline 2, and the rigidity ratio of the secondary flow corrugated pipe 6, the primary flow corrugated pipe 7 and the ring-type six-component balance 4 is designed to be less than 0.3% through design optimization software. The static thrust accurate measurement device of the jet nozzle with radial disturbance in the embodiment is integrally calibrated to obtain a balance formula, so that measurement interference of the main flow pipeline 1 and the secondary flow pipeline 2 on the ring-type six-component balance 4 is eliminated.
The present embodiment is only illustrative of the present application and does not limit the scope thereof, and those skilled in the art may make modifications to the part thereof without departing from the spirit of the application.
Claims (6)
1. The utility model provides a radial jet nozzle static thrust accurate measurement device that disturbs which characterized in that: comprises a main flow pipeline (1), a secondary flow pipeline (2), a non-force-measuring precursor (3), a ring-type six-component balance (4), a secondary flow corrugated pipe (6), a main flow corrugated pipe (7), a rectifying cone (8), a main flow rectifying device (9), a secondary flow rectifying device (10), a main flow pressure measuring rake (11), a secondary flow pressure measuring rake (12) and a force-measuring rear body injection spray pipe (13), wherein the front ends of the main flow pipeline (1), the secondary flow pipeline (2) and the non-force-measuring precursor (3) are all connected with a double-culvert ventilation support, the non-force-measuring precursor (3) is connected with the force-measuring rear body injection spray pipe (13), the main flow pipeline (1), the secondary flow pipeline (2) and the non-force-measuring precursor (3) are sequentially arranged from inside to outside, the main flow pipeline (1) is connected with the secondary flow pipeline (2) and the main flow corrugated pipe (7), the secondary flow pipeline (2) is connected with the secondary flow corrugated pipe (6) through the main flow corrugated pipe (7), the secondary flow corrugated pipe (6) is connected with the rectifying cone (8), the secondary flow corrugated pipe (6) is respectively connected with the main flow corrugated pipe (7), the six-component balance (4) and the rear body injection spray pipe (13) is sequentially arranged, the rectifying device (10) is sequentially connected with the rectifying device rear end of the main flow corrugated pipe (8), the rear end of the secondary flow rectifying device (10) is provided with a main flow pressure measuring rake (11) and a secondary flow pressure measuring rake (12).
2. The precise measurement device for the static thrust of the jet nozzle with radial disturbance according to claim 1, wherein the precise measurement device is characterized in that: a sealing ring (5) is arranged between the non-force-measuring precursor (3) and the force-measuring rear body injection nozzle (13), and the sealing ring (5) is a ring-type polytetrafluoroethylene sealing ring.
3. The precise measurement device for the static thrust of the jet nozzle with radial disturbance according to claim 2, wherein the device is characterized in that: the central axis of the ring-type six-component balance (4) is collinear with the central axis of the main flow pipeline (1), the central axes of the secondary flow corrugated pipe (6) and the main flow corrugated pipe (7) are parallel, and the central axes of the secondary flow corrugated pipe (6) and the main flow corrugated pipe (7) are respectively perpendicular to the central axis of the main flow pipeline (1).
4. A radial disturbance injection nozzle static thrust accurate measurement device according to claim 3, wherein: the pressure measuring holes of the main flow pressure measuring harrow (11) are distributed in an equal area mode, the number of the secondary flow pressure measuring harrows (12) is six, and the six secondary flow pressure measuring harrows (12) are distributed at equal intervals along the circumference of the force measuring rear body injection spray pipe (13).
5. The precise measurement device for the static thrust of the jet nozzle with radial disturbance according to claim 4, wherein the precise measurement device is characterized in that: the distance between the main flow pressure measuring rake (11) and the outlet of the main flow rectifying device (9) is larger than 1.5D, wherein D is the diameter of the main flow rectifying device (9).
6. The method is realized by the accurate measurement device for the static thrust of the jet pipe with radial disturbance according to claim 5, and is characterized by comprising the following two paths:
main flow compressed air path: the main flow compressed air enters a main flow pipeline (1) through an external double-duct ventilation support, enters a main flow corrugated pipe (7) which is radially arranged at the rear end of the main flow pipeline (1), flows to a main flow pressure measuring rake (11) after being turned by an airflow through a rectifying cone (8) and a main flow rectifying device (9), and is finally discharged by a main convergence pipe of a force measuring rear body injection jet pipe (13);
secondary flow compressed air path: the secondary flow compressed air enters the secondary flow pipeline (2) through an external double-duct ventilation support, enters a secondary flow corrugated pipe (6) which is radially arranged at the rear end of the secondary flow pipeline (2), and reaches a secondary flow pressure measuring rake (12) through a secondary flow rectifying device (10) after being turned, and secondary flow air is discharged from an outer spray pipe of a force measuring rear body jet pipe (13).
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| CN202311314624.6A CN117073969B (en) | 2023-10-12 | 2023-10-12 | Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe |
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| CN202311314624.6A CN117073969B (en) | 2023-10-12 | 2023-10-12 | Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe |
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