CN113532837A - Test tool structure for verifying pressure of special-shaped spray pipe - Google Patents
Test tool structure for verifying pressure of special-shaped spray pipe Download PDFInfo
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- CN113532837A CN113532837A CN202110954760.6A CN202110954760A CN113532837A CN 113532837 A CN113532837 A CN 113532837A CN 202110954760 A CN202110954760 A CN 202110954760A CN 113532837 A CN113532837 A CN 113532837A
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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
- G01M13/00—Testing of machine parts
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Combustion & Propulsion (AREA)
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Abstract
A test tool structure for verifying pressure of a special-shaped spray pipe comprises a simulation casing and the spray pipe connected to the air outlet end of the simulation casing, wherein a core shaft is arranged in the spray pipe; a gap is formed between the outer surface of the mandrel and the inner surface of the spray pipe to form an annular flow passage; an adapter ring for connecting a tester air source pipeline is arranged at the air inlet end of the simulation casing; an air source inlet is arranged on the adapter ring; the left end of the mandrel is fixedly connected to the adapter ring through a support column. According to the invention, the spray pipe is directly connected to the simulation casing for testing, the mandrel is arranged in the spray pipe, the annular flow channel for air flow circulation is formed according to the equal-area change rule, and the test load loading of the spray pipe is realized through the annular flow channel, so that the actual working state of the spray pipe can be simulated really, the requirement on the flow capacity of a tester is reduced, and the test pressure load condition can be met by adopting lower air flow.
Description
Technical Field
The invention relates to the technical field of pressure tests of special-shaped spray pipes of aircraft engines, in particular to a test tool structure for verifying pressure of the special-shaped spray pipes.
Background
The jet pipe of the aircraft engine is used as a main component of the engine, and the structural design reliability of the jet pipe is closely related to the working reliability of the whole engine. The special-shaped spray pipe is good in stealth comprehensive performance, but poor in pneumatic bearing capacity, and in order to verify whether the structural design of the special-shaped spray pipe meets the strength use requirement, a special-shaped casing pressure test needs to be carried out to ensure the reasonability of the design.
The strength test of the special-shaped spray pipe is carried out, the conventional pressure test method is that the adapter sections are fixedly connected to the two ends of a typical casing to form a closed cavity with the casing for carrying out load, but the adoption of the conventional pressure test tool structure inevitably brings great uncertainty to the test result due to the particularity of the installation constraint structure form of the spray pipe (the outlet end of the spray pipe is unconstrained) and the nonuniformity of the load of the spray pipe along the wall surface; meanwhile, a conventional pressure test method is adopted, the requirement on the flow capacity of the tester is high, and the test pressure load condition can be met only by high air flow.
Disclosure of Invention
The invention mainly aims to provide a test tool structure for verifying the pressure of a special-shaped spray pipe, and aims to solve the technical problem.
In order to achieve the purpose, the invention provides a test tool structure for verifying the pressure of a special-shaped spray pipe, which comprises a simulation casing and the spray pipe connected to the air outlet end of the simulation casing, wherein a core shaft is arranged in the spray pipe; a gap is formed between the outer surface of the mandrel and the inner surface of the spray pipe to form an annular flow passage; an adapter ring for connecting a tester air source pipeline is arranged at the air inlet end of the simulation casing; an air source inlet is arranged on the adapter ring; the left end of the mandrel is fixedly connected to the adapter ring through a support column.
Preferably, the annular flow passage formed by the spray pipe and the mandrel has the ratio of the area of the annular flow passage on any two cross sections to the area of the cross sections of the spray pipe on the two cross sections.
Preferably, a fixing plate for fixedly mounting the strut is arranged in the adapter ring, the fixing plate is connected to the inner wall of the adapter ring through a plurality of rib plates, and the air source inlet is formed by the interval between the adjacent rib plates.
Preferably, the strut comprises a connecting rod and mounting plates arranged at two ends of the connecting rod, and a plurality of connecting holes are respectively arranged at the positions of the mounting plates corresponding to the fixing plates; the mounting panel and the fixed plate bolted connection of pillar one end, the mounting panel of the other end with the dabber screwed connection.
Preferably, a flange ring for fixedly connecting with a tester air source pipeline is arranged at the air inlet end of the adapter ring.
Preferably, the simulation casing and the spray pipe and the simulation casing and the adapter ring are connected through bolts by adopting flange edge structures.
Preferably, an air entraining cylinder for exhausting air out of the test plant is arranged at the air outlet end of the spray pipe.
Preferably, the bleed air cylinder comprises an inlet pipe, an outlet pipe, and a convergent pipe connecting the inlet pipe and the outlet pipe; during the test, the spray pipe extends into the inlet pipe.
Preferably, a flange plate is provided at a right end portion of the gas introduction tube.
Preferably, the adapter ring, the fixing plate and the rib plate are integrally formed.
The invention has the beneficial effects that: according to the invention, the spray pipe is directly connected to the simulation casing for testing, the mandrel is arranged in the spray pipe, the annular flow channel for air flow circulation is formed according to the equal-area change rule, and the test load loading of the spray pipe is realized through the annular flow channel, so that the actual working state of the spray pipe can be simulated really, the requirement on the flow capacity of a tester is reduced, and the test pressure load condition can be met by adopting lower air flow.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic structural view of a test tool for verifying pressure of a special-shaped nozzle provided by the invention;
FIG. 2 is a schematic structural view of a nozzle of the present invention;
FIG. 3 is a schematic structural diagram of a simulation case according to the present invention;
FIG. 4 is a schematic structural view of a mandrel according to the present invention;
FIG. 5 is a schematic structural view of an adapter ring according to the present invention;
FIG. 6 is a schematic structural view of a strut in accordance with the present invention;
FIG. 7 is a schematic diagram showing the change rule of the cross-sectional areas of the mandrel and the nozzle in the present invention;
description of reference numerals: 100-simulating a case; 101-casing flange edge; 200-a spray pipe; 201-nozzle flange; 300-a transfer ring; 301-gas source inlet; 302-fixing plate; 303-ribbed plate; 304-a flange ring; 400-mandrel; 500-a pillar; 501-connecting rod; 502-a mounting plate; 600-gas introduction cylinder; 601-an inlet tube; 602-a convergent tube; 603-an outlet pipe; 604-Flange plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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 invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 1 shows a test tooling structure for verifying pressure of a special-shaped nozzle provided by the invention, which comprises a simulation casing 100 and a nozzle 200 connected to an air outlet end of the simulation casing 100, wherein a mandrel 400 is arranged in the nozzle 200; a gap exists between the outer surface of the mandrel 400 and the inner surface of the spray pipe 200 to form an annular flow passage; an adapter ring 300 for connecting a tester air source pipeline is arranged at the air inlet end of the simulation casing 100; an air source inlet 301 is arranged on the adapter ring 300; the left end of the mandrel 400 is fixedly connected to the adapter ring 300 through a support 500; the simulation casing 100 and the nozzle 200 and the simulation casing 100 and the adapter ring 300 are connected by bolts through flange structures.
Referring to fig. 2, which is a schematic structural diagram of a nozzle 200 according to the present invention, the nozzle 200 is a nozzle having a special shape, and the shapes of the cross sections are different, specifically, the air inlet end of the nozzle 200 is an oval shape, and the major axis and the minor axis of the oval are gradually shortened and the two ends of the oval are gradually tapered along the air outlet direction.
In the embodiment, the area of the annular flow passage is designed according to the equal-area change principle, that is, the ratio of the area of the annular flow passage on any two cross sections is equal to the ratio of the area of the cross sections of the nozzles on the two cross sections. The mandrel 400 is inserted into the nozzle 200, an annular flow passage is formed between the outer surface of the mandrel 400 and the inner surface of the nozzle 200, and during testing, when air flows through the annular flow passage, the test load loading of the nozzle 200 is realized. Referring specifically to fig. 7, any two cross-sections are the first cross-section and the second cross-section illustrated in fig. 7, the first cross-section being selected at the outlet end face of the nozzle 200, and the second cross-section being selected at a position near the middle of the nozzle 200. On the first cross section, the area of the annular flow passage is A, and the area of the cross section of the spray pipe 200 is B; in the second cross-section, the area of the annular flow passage is a1, the cross-sectional area of the nozzle 200 is B1, and the ratio of a to a1 is equal to the ratio of B to B1 (i.e., a/a1 is equal to B/B1). The first cross section and the second cross section may be selected from any position, and are not limited to the positions shown in fig. 7.
The area of the annular flow channel is converted and selected according to the load requirement and the actual capacity of the tester, and the selection method is determined according to the following formula:
wherein: m is the tester flow;
p is total pressure of the inlet of the spray pipe;
a is an annular flow channel in any cross-section (shown in FIG. 7 as a first cross-section);
q (λ) is a flow function;
t is the total gas temperature.
By the calculation method, the area of the annular flow channel can be calculated according to the actual capacity of the tester, and the section size of the mandrel 400 is further determined.
As shown in fig. 5, which is a schematic structural diagram of the adapter ring 300, in this embodiment, a fixing plate 302 for fixedly mounting the strut 500 is disposed inside the adapter ring 300, the fixing plate 302 is connected to an inner wall of the adapter ring 300 through a plurality of ribs 303, and an interval between adjacent ribs 303 forms the gas source inlet 301. A flange ring 304 for fixedly connecting with a tester air source pipeline is arranged at the air inlet end of the adapter ring 300. The adapter ring 300, the fixing plate 302 and the rib plate 303 are integrally formed.
As shown in fig. 6, in the present embodiment, the strut 500 includes a connecting rod 501 and mounting plates 502 disposed at both ends of the connecting rod 501, and a plurality of connecting holes are respectively disposed at positions of the mounting plates 502 corresponding to the fixing plates 302; the mounting plate 502 of one end of the strut 500 is bolted to the fixing plate 302, and the mounting plate 502 of the other end is screwed to the stem 400.
In this embodiment, a bleed air cylinder 600 for discharging air out of the test plant is provided at the air outlet end of the nozzle 200. The gas introduction tube 600 includes an inlet tube 601, an outlet tube 603, and a converging tube 602 connecting the inlet tube 601 and the outlet tube 603; during the test, the nozzle 200 extends into the inlet pipe 601. A flange plate 604 is provided at the right end of the gas introduction tube 600. Through setting up convergent pipe 602, can converge gas gradually to discharge the test factory building.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. The utility model provides a verify experimental frock structure of abnormal shape spray tube pressure, includes simulation machine casket (100) and connects spray tube (200) of giving vent to anger the end at simulation machine casket (100), its characterized in that:
a mandrel (400) is arranged in the spray pipe (200); a gap exists between the outer surface of the mandrel (400) and the inner surface of the spray pipe (200) to form an annular flow passage;
an adapter ring (300) for connecting a tester air source pipeline is arranged at the air inlet end of the simulation casing (100); an air source inlet (301) is arranged on the adapter ring (300);
the left end of the mandrel (400) is fixedly connected to the adapter ring (300) through a support column (500).
2. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 1, characterized in that: the annular flow channel formed by the spray pipe (200) and the mandrel (400) has the area ratio of the annular flow channel on any two cross sections equal to the area ratio of the cross sections of the spray pipe on the two cross sections.
3. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 1, characterized in that: the fixing plate (302) used for fixedly mounting the support column (500) is arranged in the adapter ring (300), the fixing plate (302) is connected to the inner wall of the adapter ring (300) through a plurality of ribbed plates (303), and the air source inlets (301) are formed by the intervals between the adjacent ribbed plates (303).
4. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 3, characterized in that: the strut (500) comprises a connecting rod (501) and mounting plates (502) arranged at two ends of the connecting rod (501), and a plurality of connecting holes are respectively arranged at the positions of the mounting plates (502) corresponding to the fixing plates (302); the mounting plate (502) at one end of the strut (500) is connected with the fixing plate (302) through bolts, and the mounting plate (502) at the other end of the strut is connected with the mandrel (400) through screws.
5. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 1, characterized in that: and a flange ring (304) for fixedly connecting with a tester air source pipeline is arranged at the air inlet end of the adapter ring (300).
6. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 1, characterized in that: and the simulation casing (100) and the spray pipe (200) as well as the simulation casing (100) and the adapter ring (300) are connected by adopting flange edge structures for bolts.
7. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 1, characterized in that: and an air guide cylinder (600) for discharging air out of the test plant is arranged at the air outlet end of the spray pipe (200).
8. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 7, characterized in that: the gas introducing cylinder (600) comprises an inlet pipe (601), an outlet pipe (603) and a convergent pipe (602) connecting the inlet pipe (601) and the outlet pipe (603); during the test, the spray pipe (200) extends into the inlet pipe (601).
9. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 7, characterized in that: a flange plate (604) is arranged at the right end part of the gas introducing cylinder (600).
10. The test tool structure for verifying the pressure of the special-shaped spray pipe according to claim 3, characterized in that: the adapter ring (300), the fixing plate (302) and the rib plate (303) are integrally formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110954760.6A CN113532837B (en) | 2021-08-19 | 2021-08-19 | Test tool structure for verifying pressure of special-shaped spray pipe |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110954760.6A CN113532837B (en) | 2021-08-19 | 2021-08-19 | Test tool structure for verifying pressure of special-shaped spray pipe |
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| CN113532837A true CN113532837A (en) | 2021-10-22 |
| CN113532837B CN113532837B (en) | 2022-11-18 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526919A (en) * | 2022-02-21 | 2022-05-24 | 中国航发贵阳发动机设计研究所 | Test method and tool for verifying strength of special-shaped jet pipe of aircraft engine |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2836925A1 (en) * | 1978-08-24 | 1980-03-20 | Volkswagenwerk Ag | Ring chamber tester for combustion engine's valve seat - uses air blown through nozzles in inserted ring mandrel |
| CN102493894A (en) * | 2011-11-18 | 2012-06-13 | 南京航空航天大学 | Nozzle exhaust mixing method and device based on pneumatic tab technique |
| CN102744166A (en) * | 2012-07-04 | 2012-10-24 | 大连理工大学 | Core-adjustable variable-cross-section-tube ultrasonic condensation cyclone separator |
| CN205991885U (en) * | 2016-08-31 | 2017-03-01 | 北京航天三发高科技有限公司 | A kind of exhaust apparatus of supersonic speed nozzle aerofluxuss simulation test |
| CN108051214A (en) * | 2018-01-15 | 2018-05-18 | 佛山特博科技有限公司 | A kind of foil dynamical pressure air journal bearing is performance test bed |
| CN109225694A (en) * | 2018-09-30 | 2019-01-18 | 南昌大学 | Adjustable melange effect deashing device for pulse blow filter |
| CN109606644A (en) * | 2018-12-13 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of asymmetric exhaust structure of lift fan |
| US20190137362A1 (en) * | 2017-11-08 | 2019-05-09 | Safran Aircraft Engines | Ground testing device for a turbomachine |
| CN111577480A (en) * | 2020-05-26 | 2020-08-25 | 中国航发沈阳发动机研究所 | Low detectable integration spray tube suitable for self-adaptation engine |
| US20200332741A1 (en) * | 2017-12-19 | 2020-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Thrust nozzle for a turbofan engine on a supersonic aircraft |
| CN112555058A (en) * | 2021-02-19 | 2021-03-26 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
| CN112855629A (en) * | 2021-03-04 | 2021-05-28 | 郭孝国 | Gas ejector |
-
2021
- 2021-08-19 CN CN202110954760.6A patent/CN113532837B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2836925A1 (en) * | 1978-08-24 | 1980-03-20 | Volkswagenwerk Ag | Ring chamber tester for combustion engine's valve seat - uses air blown through nozzles in inserted ring mandrel |
| CN102493894A (en) * | 2011-11-18 | 2012-06-13 | 南京航空航天大学 | Nozzle exhaust mixing method and device based on pneumatic tab technique |
| CN102744166A (en) * | 2012-07-04 | 2012-10-24 | 大连理工大学 | Core-adjustable variable-cross-section-tube ultrasonic condensation cyclone separator |
| CN205991885U (en) * | 2016-08-31 | 2017-03-01 | 北京航天三发高科技有限公司 | A kind of exhaust apparatus of supersonic speed nozzle aerofluxuss simulation test |
| US20190137362A1 (en) * | 2017-11-08 | 2019-05-09 | Safran Aircraft Engines | Ground testing device for a turbomachine |
| US20200332741A1 (en) * | 2017-12-19 | 2020-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Thrust nozzle for a turbofan engine on a supersonic aircraft |
| CN108051214A (en) * | 2018-01-15 | 2018-05-18 | 佛山特博科技有限公司 | A kind of foil dynamical pressure air journal bearing is performance test bed |
| CN109225694A (en) * | 2018-09-30 | 2019-01-18 | 南昌大学 | Adjustable melange effect deashing device for pulse blow filter |
| CN109606644A (en) * | 2018-12-13 | 2019-04-12 | 中国航发沈阳发动机研究所 | A kind of asymmetric exhaust structure of lift fan |
| CN111577480A (en) * | 2020-05-26 | 2020-08-25 | 中国航发沈阳发动机研究所 | Low detectable integration spray tube suitable for self-adaptation engine |
| CN112555058A (en) * | 2021-02-19 | 2021-03-26 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
| CN112855629A (en) * | 2021-03-04 | 2021-05-28 | 郭孝国 | Gas ejector |
Non-Patent Citations (5)
| Title |
|---|
| ZHANG YINGLI: ""kinematics simulation of an aeroengine convergent/divergent adjustable exhaust nozzle"", 《DISCOVERY，INNOVATION AND COMMUNICATION-5TH CSAA SCIENCEAND TECHNOLOGY YOUTH FORUM》 * |
| 张海波等: "轴对称矢量喷管作动系统矢量偏转受载特性研究", 《南京航空航天大学学报》 * |
| 张翔: ""拉瓦尔喷管喉部区域当量直径液力测量方法"", 《兵工学报》 * |
| 李环等: "基于DOE的某异型喷管结构优化减重研究", 《南京航空航天大学学报》 * |
| 章伯其: "超音速环状喷管设计", 《弹道学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526919A (en) * | 2022-02-21 | 2022-05-24 | 中国航发贵阳发动机设计研究所 | Test method and tool for verifying strength of special-shaped jet pipe of aircraft engine |
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| CN113532837B (en) | 2022-11-18 |
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