CN113063666B - Aeroengine casing pressure test tool and using method thereof - Google Patents
Aeroengine casing pressure test tool and using method thereof Download PDFInfo
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- CN113063666B CN113063666B CN202110357590.3A CN202110357590A CN113063666B CN 113063666 B CN113063666 B CN 113063666B CN 202110357590 A CN202110357590 A CN 202110357590A CN 113063666 B CN113063666 B CN 113063666B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0003—Steady
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0017—Tensile
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0019—Compressive
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0042—Pneumatic or hydraulic means
- G01N2203/0048—Hydraulic means
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Abstract
The invention relates to an aeroengine casing pressure test tool and a using method thereof, the aeroengine casing pressure test tool comprises a sealing base, a switching cylinder, a limiting cylinder, a sliding sealing plug and an upper cylinder, wherein the limiting cylinder comprises an upper force transmission section and a lower force transmission section, the sliding sealing plug comprises a lower sliding disc, an upper sliding disc and a connecting column, the lower sliding disc is in sliding and sealing fit with the inner wall of the upper force transmission section, the upper sliding disc is in sliding and sealing fit with the inner wall of the upper cylinder, the connecting column is used for connecting the lower sliding disc and the upper sliding disc, the upper part of the upper force transmission section is provided with an upper force transmission boss for limiting the lower sliding disc, the upper part of the lower force transmission section is provided with a lower force transmission boss for limiting the lower sliding disc, the lower sliding disc is arranged in the upper force transmission section, a pressure regulating cavity is formed between the upper sliding disc and the top wall of the upper cylinder, and a load containing cavity is formed between the lower sliding disc and the upper force transmission section, the lower force transmission section, the casing to be tested, the switching cylinder and the sealing base.
Description
Technical Field
The invention relates to the technical field of detection of an aeroengine casing, in particular to a pressure test tool for the aeroengine casing and a using method thereof.
Background
The aero-engine case needs to have enough strength reserve, does not crack and has small deformation under the condition of bearing larger gas pressure, so that the case needs to be subjected to a pressure test to verify whether the strength of the case is enough; the aircraft engine casing is usually a cylindrical structure, and the casing bears outward radial gas pressure and axial tension when working. During a pressure test, the stress state of the casing during operation needs to be simulated, so that the casing can bear radial force and axial force simultaneously. According to the existing pressure test method, a sealing tool is usually adopted to seal a casing, and then hydraulic oil is loaded for testing, the method can usually ensure that the loading of radial force meets the requirement, but the problem of additional axial force is generated, and the axial force cannot be adjusted; or when the pressure test is carried out, an axial force loading instrument is selected to load the axial force on the casing, and the test equipment is complex.
Disclosure of Invention
The invention aims to provide an aero-engine casing pressure test tool which is simple in structure, easy to install, convenient to operate and capable of adjusting axial force and a using method thereof.
In order to solve the technical problems, the aeroengine casing pressure test tool provided by the invention comprises a sealing base, a switching cylinder, a limiting cylinder, a sliding sealing plug and an upper cylinder, wherein the limiting cylinder comprises an upper force transmission section and a lower force transmission section, the sliding sealing plug comprises a lower sliding disc, an upper sliding disc and a connecting column, the lower sliding disc is in sliding and sealing fit with the inner wall of the upper force transmission section, the upper sliding disc is in sliding and sealing fit with the inner wall of the upper cylinder, the connecting column is used for connecting the lower sliding disc and the upper sliding disc, the upper part of the upper force transmission section is provided with an upper force transmission boss for limiting the lower sliding disc, the upper part of the lower force transmission section is provided with a lower force transmission boss for limiting the lower sliding disc, and the bottom end of the switching cylinder is in sealing connection with the sealing base when the aeroengine casing pressure test tool is used, the top end of the switching cylinder body is connected with the bottom end of the tested casing in a sealing mode, the top end of the tested casing is connected with the bottom end of the lower force transmission section in a sealing mode, the top end of the lower force transmission section is connected with the bottom end of the upper force transmission section in a sealing mode, the lower sliding disc is arranged in the upper force transmission section, the upper sliding disc is arranged in the upper cylinder body, a pressure regulating cavity is formed between the upper sliding disc and the top wall of the upper cylinder body, a load containing cavity is formed between the lower sliding disc and the upper force transmission section, the tested casing, the switching cylinder body and the sealing base, an upper oil inlet communicated with the pressure regulating cavity is formed in the upper cylinder body, a lower oil inlet communicated with the load containing cavity is formed in the sealing base, and a plurality of pull rods used for limiting the upper cylinder body and the sealing base are arranged between the upper cylinder body and the sealing base.
Further, the outer wall of the lower sliding disc is provided with a first inner ring groove, a first sealing ring is arranged in the first inner ring groove, and sliding sealing fit is formed between the first sealing ring and the upper force transmission section.
Further, the outer wall of the upper sliding disc is provided with a second inner ring groove, a second sealing ring is arranged in the second inner ring groove, and sliding sealing fit is formed between the second sealing ring and the inner wall of the upper cylinder body.
Further, the top of pull rod sets up the last screw rod with first lock nut screw-thread fit, and the downside of going up the screw rod sets up upper limit boss, and the bottom of pull rod sets up the lower screw rod with first lock nut screw-thread fit, and the upside of lower screw rod sets up down limit boss, is injectd the distance between last barrel and the seal base by upper limit boss and first lock nut, lower limit boss and first lock nut.
Furthermore, the two ends of the switching cylinder body are respectively provided with a connecting outer ring platform in an outward protruding mode, the two ends of the tested casing are respectively provided with a casing outer ring platform in an outward protruding mode, the connecting outer ring platform is provided with a screw hole, and the connecting outer ring platform is in sealing connection with the sealing base and the casing outer ring platform.
Furthermore, the two ends of the lower force transmission section are respectively provided with a lower force transmission outer ring platform in a protruding mode towards the outside, a screw hole is formed in the lower force transmission outer ring platform, and the lower force transmission outer ring platform is connected with the outer ring platform of the casing in a sealing mode.
Furthermore, the top end of the lower force transmission section is inwards provided with a lower force transmission inner annular table in a protruding mode so as to form a lower force transmission boss; the bottom end of the upper force transmission section is outwards protruded with an upper force transmission outer ring platform, and the upper force transmission outer ring platform and the lower force transmission outer ring platform are in sealed connection; and the top end of the upper force transmission section is inwards provided with an upper force transmission inner annular table in a protruding mode so as to form an upper force transmission boss.
The using method of the aircraft engine casing pressure test tool comprises the following steps that when the tested casing requires pressure loading and axial tension, hydraulic oil is loaded to the load containing cavity through the lower oil inlet interface, so that the load containing cavity reaches the required pressure; the lower sliding disc of the sliding sealing plug slides to the upper force transmission section under the action of pressure and is close to the upper force transmission boss, the lower sliding disc transmits the pulling force to the tested case through the upper force transmission section and the lower force transmission section, so that the tested case is under the action of the pulling force, hydraulic oil is loaded into the pressure regulating cavity through the upper oil inlet interface, and the magnitude of the pulling force borne by the tested case is changed by regulating the oil pressure in the pressure regulating cavity; when the tested case requires pressure loading and axial pressure, hydraulic oil is injected into the pressure regulating cavity through the upper oil inlet interface, so that the lower sliding disc of the sliding sealing plug slides down to the downward force transmission section under the action of pressure and is tightly close to the lower force transmission boss, the lower sliding disc is transmitted to the tested case through the lower force transmission boss, the tested case bears the pressure, the hydraulic oil is loaded into the load cavity through the lower oil inlet interface, the load cavity reaches the required pressure, and the pressure of the tested case is changed by adjusting the oil pressure in the pressure regulating cavity; when the tested case requires loading pressure and the axial force is zero, hydraulic oil with a certain volume is injected into the pressure regulating cavity through the upper oil inlet interface, so that the lower sliding disc of the sliding sealing plug is positioned in the middle of the lower force transmission boss and the upper force transmission boss, the pressure regulating cavity is sealed, the volume of the hydraulic oil in the pressure regulating cavity is ensured to be unchanged, the hydraulic oil is injected into the load containing cavity through the lower oil inlet interface, the load containing cavity is enabled to reach the required pressure, and the tested case is enabled not to bear the axial force while the tested case reaches the test required pressure.
The invention has the technical effects that: (1) Compared with the prior art, the pressure test tool for the aero-engine casing is provided with the pressure regulating cavity, the limiting cylinder and the sliding sealing plug device, and the axial pressure or the tensile force borne by the tested casing can be adjusted by adjusting the hydraulic oil pressure in the pressure regulating cavity; (2) Compared with the loading instrument for loading the axial force, the tool is simple in structure, can be adaptively changed according to the actual size and shape of the casing, and is wide in applicability; (3) The hydraulic oil pressure in the limiting cylinder can be adjusted with high precision, so that high-precision adjustment of the axial force is realized.
Drawings
The invention is described in further detail below with reference to the drawings of the specification:
FIG. 1 is a schematic sectional structure diagram of an aircraft engine casing pressure test tool;
FIG. 2 is a schematic diagram of a partial sectional structure of a pressure test tool for an aircraft engine casing;
FIG. 3 is a schematic cross-sectional view of the assembled spacing cylinder and sliding sealing plug;
FIG. 4 is a schematic cross-sectional structure diagram of an aircraft engine casing pressure test tool in use;
FIG. 5 is a schematic view of the use state of the aircraft engine casing pressure test tool when the casing is loaded with pressure and axial tension;
FIG. 6 is a schematic view of the use state of the aircraft engine casing pressure test tool when the casing is loaded with pressure and axial pressure;
in the figure:
the device comprises a sealing base 1, a lower oil inlet interface 11, a switching cylinder 2, a tested casing 3, a load containing cavity 31, a limiting cylinder 4, a lower force transmission section 41, an upper force transmission section 42, a lower force transmission boss 43, an upper force transmission boss 44, a pull rod 5, a lower limiting boss 51, an upper limiting boss 52, a first locking nut 53, a sliding sealing plug 6, a lower sliding disc 61, an upper sliding disc 62, a first sealing ring 63, a second sealing ring 64, an upper cylinder 7, an upper oil inlet interface 71, a pressure regulating containing cavity 72, a locking screw 8 and a second locking nut 81.
Detailed Description
Example 1
As shown in fig. 1 to 4, the aeroengine casing pressure test tool of the embodiment includes a sealing base 1, a switching cylinder 2, a limiting cylinder 4, a sliding sealing plug 6 and an upper cylinder 7, where the sealing base 1 includes a disc-shaped sealing portion and a cylindrical supporting portion, two ends of the switching cylinder 2 respectively protrude outwards to form a connecting outer ring platform, two ends of a tested casing 3 respectively protrude outwards to form a casing outer ring platform, 8 screw holes are uniformly distributed on the same circumference of the connecting outer ring platform, the sealing portion is provided with 8 through holes matched with the screw holes on the same circumference, and the connecting outer ring platform at the bottom end contacts with the sealing portion of the sealing base 1 and is fixed by a locking screw and a locking nut to realize sealing connection; the outer ring platform of the casing is also provided with a through hole, and the outer ring platform of the casing is contacted with the outer ring platform of the casing at the top end and fixed by a locking screw rod and a locking nut to realize sealing connection.
The limiting cylinder 4 comprises an upper force transmission section 41 and a lower force transmission section 42 which have the same inner diameter and outer diameter, the sliding sealing plug 6 comprises a lower sliding disc 61 which is in sliding and sealing fit with the inner wall of the upper force transmission section 41, an upper sliding disc 62 which is in sliding and sealing fit with the inner wall of the upper cylinder 7, and a connecting column which is used for connecting the lower sliding disc 61 and the upper sliding disc 62, a first inner ring groove is formed in the outer wall of the lower sliding disc 61, a first sealing ring 63 is arranged in the first inner ring groove, and sliding sealing fit is formed between the first sealing ring 63 and the upper force transmission section 42; the outer wall of the upper sliding disc 62 is provided with a second inner ring groove, a second sealing ring 64 is arranged in the second inner ring groove, and a sliding sealing fit is formed between the second sealing ring 64 and the inner wall of the upper cylinder 7. The top end of the connecting column is fixedly connected with the center of the bottom surface of the upper sliding tray 62, and the bottom end of the connecting column is in threaded connection with the center of the top surface of the lower sliding tray 61.
The top end of the upper force transmission section 42 is provided with an upper force transmission inner annular table in an inward protruding mode to form an upper force transmission boss 44 used for limiting the lower sliding disc 61, and a connecting column extends out of the center of the upper force transmission inner annular table; the bottom end of the upper force transmission section 42 is outwards protruded to form an upper force transmission outer ring platform, 8 screw holes are uniformly distributed on the same circumference of the upper force transmission outer ring platform, two ends of the lower force transmission section 41 are respectively outwards protruded to form a lower force transmission outer ring platform, 8 through holes matched with the screw holes are uniformly distributed on the same circumference of the lower force transmission outer ring platform at the top, and the upper force transmission outer ring platform is in contact with the lower force transmission outer ring platform at the top and is fixed through a locking screw 8 and a second locking nut 81 to realize sealing connection; the top end of the lower force transmission section 41 is inwards provided with a lower force transmission inner annular platform in a protruding mode to form a lower force transmission boss 43, 8 screw holes are evenly distributed on the same circumference of a casing outer annular platform at the top of the tested casing 3, 8 through holes matched with the screw holes are evenly distributed on the same circumference of a lower force transmission outer annular platform at the bottom of the lower force transmission section 41, and the lower force transmission outer annular platform 41 is in contact with the casing outer annular platform at the top of the tested casing 3 and is fixed through a locking screw and a locking nut to achieve sealing connection.
Go up and set up 8 between barrel 7 and the sealing base 1 and be used for carrying out spacing pull rod 5 to last barrel 7 and sealing base 1, 8 first screws of equipartition on same circumference on the roof of last barrel 7, 8 through-holes with first screw one-to-one of equipartition on the sealing of sealing base 1 on same circumference, the top of pull rod 5 sets up the last screw rod with first lock nut 53 screw-thread fit, the downside of going up the screw rod sets up spacing boss 52, the bottom of pull rod 5 sets up the lower screw rod with first lock nut 53 screw-thread fit, the upside of lower screw rod sets up down spacing boss 51, go up the screw rod and stretch out first screw, the through-hole is stretched out to lower screw rod, by last spacing boss 52 and first lock nut 53, lower spacing boss 51 and first lock nut 53 are injectd the distance between barrel 7 and the sealing base 1.
When the device is used, the bottom end of the switching cylinder body 2 is hermetically connected with the sealing base 1, the top end of the switching cylinder body 2 is hermetically connected with the bottom end of the tested casing 3, the top end of the tested casing 3 is hermetically connected with the bottom end of the lower force transmission section 41, the top end of the lower force transmission section 41 is hermetically connected with the bottom end of the upper force transmission section 42, the lower sliding disc 61 is arranged in the upper force transmission section 42, the upper sliding disc 62 is arranged in the upper cylinder body 7, a pressure regulating cavity 72 is formed between the upper sliding disc 62 and the top wall of the upper cylinder body 7, a load cavity 31 is formed between the lower sliding disc 61 and the upper force transmission section 42, the lower force transmission section 41, the tested casing 3, the switching cylinder body 2 and the sealing base 1, an upper oil inlet port 71 communicated with the pressure regulating cavity 72 is arranged on the upper cylinder body 7, and a lower oil inlet port 11 communicated with the load cavity 31 is arranged on the sealing base 1.
Example 2
The using method of the aircraft engine casing pressure test tool comprises the following steps that when the tested casing 3 requires pressure loading and axial tension, as shown in fig. 5, hydraulic oil is loaded to the load containing cavity 31 through the lower oil inlet interface 71, so that the load containing cavity 31 reaches the required pressure P 31 (ii) a Below the sliding sealing plug 6The sliding disc 61 slides down to the upper force transmission section 42 under the action of pressure and is close to the upper force transmission boss 44, the lower sliding disc 62 transmits pulling force to the tested casing 3 through the upper force transmission section 42 and the lower force transmission section 41, so that the tested casing 3 is under the action of the pulling force, hydraulic oil is loaded into the pressure regulating cavity 72 through the upper oil inlet connector 11, and the oil pressure P in the pressure regulating cavity 72 is adjusted 72 Changing the tension F to which the tested case 3 is subjected L Size; tensile force F L The calculation formula is shown as formula (1).
When the tested casing 3 requires to be loaded with pressure and axial pressure, as shown in fig. 6, hydraulic oil is injected into the pressure regulating cavity 72 through the upper oil inlet port 71, and the pressure is P 72 The lower sliding disc 61 of the sliding sealing plug 6 slides down the downward force transmission section 41 under the action of pressure and is tightly close to the downward force transmission boss 43, the lower sliding disc 61 is transmitted to the tested case 3 through the downward force transmission boss 43, the tested case 3 bears the pressure, hydraulic oil is loaded into the load accommodating cavity 31 through the lower oil inlet interface 11, the load accommodating cavity 31 reaches the required pressure, and the pressure F borne by the tested case 3 is changed by adjusting the oil pressure in the pressure regulating accommodating cavity 72 Y The size of (d); pressure F Y The calculation formula is shown in formula (2).
When the tested case 3 requires loading pressure and the axial force is zero, a certain volume of hydraulic oil is injected into the pressure regulating cavity 72 through the upper oil inlet interface 71, the volume V calculation formula of the hydraulic oil is shown in formulas (3), (4) and (5), so that the lower sliding disc 61 of the sliding sealing plug 6 is positioned in the middle of the lower force transmission boss 43 and the upper force transmission boss 44, the pressure regulating cavity 72 is sealed, the volume of the hydraulic oil in the pressure regulating cavity 72 is ensured to be unchanged, the hydraulic oil is injected into the load cavity 31 through the lower oil inlet interface 11, and the load cavity 31 is enabled to reach the required pressure, so that the tested case 3 is ensured not to bear the axial force while the tested case 3 reaches the test required pressure.
It should be understood that the above examples are only for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And such obvious variations or modifications which fall within the spirit of the invention are intended to be covered by the scope of the present invention.
Claims (7)
1. The utility model provides an aeroengine machine casket pressure test frock, its characterized in that, includes sealing base, switching barrel, spacing barrel, slip sealing plug and last barrel, spacing barrel includes power transmission section and power transmission section down, the slip sealing plug include with last power transmission section inner wall slip and seal fit's slide down, with last barrel inner wall slip and seal fit's slide up, be used for connecting slide down and the spliced pole of slide up, the upper portion of going up the power transmission section sets up and carries out spacing last power boss to the slide down, the upper portion of power transmission section sets up and carries out spacing lower power boss to the slide down, during the use the bottom and the sealing base sealing connection of switching barrel, the top and the bottom sealing connection of being surveyed the machine casket of switching barrel are connected with the bottom sealing of power transmission section down, and the bottom sealing connection of going up the power transmission section down, and the slide down is arranged in the power transmission section, and the upper slide is arranged in the upper barrel by last slide and is formed between upper slide and the upper barrel roof and the power transmission section, the oil feed is arranged and is connected with the pressure regulating barrel and is used for communicating with the sealed interface that the pressure regulating barrel sets up and the sealed connection of the oil feed transmission section.
2. The aircraft engine casing pressure test tool according to claim 1, wherein a first inner annular groove is formed in the outer wall of the lower sliding plate, a first sealing ring is arranged in the first inner annular groove, and sliding sealing fit is formed between the first sealing ring and the upper power transmission section.
3. The aircraft engine casing pressure test tool according to claim 2, wherein a second inner annular groove is formed in the outer wall of the upper sliding disc, a second sealing ring is arranged in the second inner annular groove, and sliding sealing fit is formed between the second sealing ring and the inner wall of the upper cylinder body.
4. The aircraft engine casing pressure test tool according to claim 2, wherein an upper screw rod in threaded fit with the first locking nut is arranged at the top end of the pull rod, an upper limiting boss is arranged on the lower side of the upper screw rod, a lower screw rod in threaded fit with the first locking nut is arranged at the bottom end of the pull rod, a lower limiting boss is arranged on the upper side of the lower screw rod, and the distance between the upper cylinder and the sealing base is limited by the upper limiting boss, the first locking nut, the lower limiting boss and the first locking nut.
5. The aeroengine casing pressure test tool of claim 4, wherein the two ends of the switching cylinder respectively protrude outwards to form a connecting outer ring platform, the two ends of the tested casing respectively protrude outwards to form a casing outer ring platform, the connecting outer ring platform is provided with a screw hole, and the connecting outer ring platform is in sealing connection with the sealing base and the casing outer ring platform.
6. The aeroengine casing pressure test tool according to claim 5, wherein the two ends of the lower force transmission section respectively protrude outwards to form a lower force transmission outer ring platform, the lower force transmission outer ring platform is provided with screw holes, and the lower force transmission outer ring platform is in sealing connection with the casing outer ring platform.
7. The aeroengine case pressure test tool of claim 6, wherein the top end of the lower force transfer section is provided with a lower force transfer inner annular table protruding inwards to form a lower force transfer boss; the bottom end of the upper force transmission section is outwards protruded with an upper force transmission outer ring platform, and the upper force transmission outer ring platform and the lower force transmission outer ring platform are in sealed connection; and the top end of the upper force transmission section is inwards provided with an upper force transmission inner annular table in a protruding mode so as to form an upper force transmission boss.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310001708.8A CN116086968A (en) | 2021-04-01 | 2021-04-01 | Aeroengine casing pressure test tool |
| CN202110357590.3A CN113063666B (en) | 2021-04-01 | 2021-04-01 | Aeroengine casing pressure test tool and using method thereof |
| CN202310001809.5A CN116026695A (en) | 2021-04-01 | 2021-04-01 | Application method of aeroengine casing pressure test tool |
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| CN202110357590.3A CN113063666B (en) | 2021-04-01 | 2021-04-01 | Aeroengine casing pressure test tool and using method thereof |
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| CN202310001809.5A Division CN116026695A (en) | 2021-04-01 | 2021-04-01 | Application method of aeroengine casing pressure test tool |
| CN202310001708.8A Division CN116086968A (en) | 2021-04-01 | 2021-04-01 | Aeroengine casing pressure test tool |
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| CN202310001809.5A Pending CN116026695A (en) | 2021-04-01 | 2021-04-01 | Application method of aeroengine casing pressure test tool |
| CN202310001708.8A Pending CN116086968A (en) | 2021-04-01 | 2021-04-01 | Aeroengine casing pressure test tool |
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| CN202310001708.8A Pending CN116086968A (en) | 2021-04-01 | 2021-04-01 | Aeroengine casing pressure test tool |
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| CN113776950A (en) * | 2021-08-16 | 2021-12-10 | 中国航发贵阳发动机设计研究所 | Water bag structure for pressure test of special-shaped casing and mounting method thereof |
| CN116008090B (en) * | 2023-02-16 | 2023-06-23 | 北京成立科技有限公司 | Aeroengine combustion chamber casing internal pressure test device |
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| CN116026695A (en) | 2023-04-28 |
| CN116086968A (en) | 2023-05-09 |
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