CN111678646B - Engine transition bearing cavity tightness inspection device - Google Patents
Engine transition bearing cavity tightness inspection device Download PDFInfo
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- CN111678646B CN111678646B CN202010555806.2A CN202010555806A CN111678646B CN 111678646 B CN111678646 B CN 111678646B CN 202010555806 A CN202010555806 A CN 202010555806A CN 111678646 B CN111678646 B CN 111678646B
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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
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/025—Details with respect to the testing of engines or engine 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
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
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- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application provides an engine transition bearing chamber leakproofness inspection device, it includes: the front baffle assembly is formed by connecting a front baffle and a front sealing cover through a connecting piece, the rear baffle assembly is formed by fixedly connecting a rear baffle and a rear end cover, and the pull rod is arranged on the rear baffle assembly; the pull rod penetrates through the low-turbine shaft to fix the front baffle plate assembly and the rear baffle plate assembly on the low-turbine rotor assembly, so that the first end face and the fifth end face are sealed; the front sealing cover is provided with a horizontal longitudinal mounting edge, a front sealing gasket is arranged in the horizontal longitudinal mounting edge, the horizontal longitudinal mounting edge forms a bolt pressing structure for connecting with the front baffle, and the bolt pressing structure is superposed with the interference fit between the front sealing cover and the front sealing gasket to realize the pressing and sealing of the cylindrical surface at the second end face position of the low turbine shaft; a vent hole at the second end surface of the low turbine shaft and a plug in interference fit with the rear fourth end surface of the oil collecting ring are arranged; the rear baffle is provided with an air bleed hole, an oil inlet hole and an oil bleed hole, and is used for providing a channel for air to flow out and providing an oil supply interface and discharging and recovering lubricating oil.
Description
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a device for checking the sealing performance of a transition bearing cavity of an engine.
Background
As shown in fig. 1, a fulcrum bearing in the aircraft engine is a transition bearing 2, an inner ring of the transition bearing 2 is supported on a high-pressure turbine rotor (not shown), an outer ring of the transition bearing 2 is supported on a low-pressure turbine rotor, and a bearing cavity (i.e., a front bearing cavity 11) in which the transition bearing 2 is located is composed of a sealing structure between the rotating low-pressure turbine rotor and the high-pressure turbine rotor, and is communicated with a rear bearing cavity 12.
Limited by the structure, the leakproofness of transition bearing chamber is in many positions, it includes first terminal surface K1 of low pressure turbine rotor subassembly front end, low pressure turbine shaft 1 axle body end cylinder K2, low pressure turbine shaft axis body air vent step terminal surface K3, receive oil ring rear end face K4 and rear end face K5 of back fulcrum runway 13 in the low pressure turbine rotor subassembly, sealed position structure is mostly the thin wall spare (gyration with axis 3), easy production is out of shape after the atress, and there are the leakproofness inspection operability subalternation problem, this just leads to good bad inspection control means that lacks always of transition turbine bearing chamber leakproofness, make in the engine actual working process, there are the problem that the oil leak of low pressure turbine bearing chamber is great, the big consumption of lubricating oil.
The existing engine sealing inspection process is mostly used for carrying out the sealing inspection of a stator assembly, and because the design structure of a stator assembly sealing cavity is generally simpler and is open, the corresponding sealing inspection process adopts the simple end cover design and cannot be applied to the sealing position of the transition bearing cavity, and the rest of the few annular sealing processes are mostly of an integral structure, if the sealing inspection process is used for the working condition that the shaft head of the low-pressure turbine is far away from the sealing cavity, the sealing inspection process needs to be sleeved from the far-end shaft head, and the problems of difficult installation, complex technological process and the like exist.
Disclosure of Invention
It is an object of the present application to provide an engine transition bearing cavity tightness check device to solve or mitigate at least one of the problems of the background art.
The technical scheme of the application is as follows: an engine transition bearing cavity tightness inspection device, comprising:
the front baffle assembly is formed by connecting a front baffle and a front sealing cover through a connecting piece, the rear baffle assembly is formed by fixedly connecting a rear baffle and a rear end cover, and the pull rod is arranged on the rear baffle assembly;
the pull rod penetrates through the low-turbine shaft connecting bolt hole and fixes the front baffle plate assembly and the rear baffle plate assembly on the low-turbine rotor assembly through the compression nut, so that the first end face and the fifth end face are sealed;
the front sealing cover is provided with a horizontal longitudinal mounting edge, a front sealing gasket is arranged in the horizontal longitudinal mounting edge, the horizontal longitudinal mounting edge forms a bolt compression structure for connecting with the front baffle, and the bolt compression structure is superposed with the wedge-shaped interference fit between the front sealing cover and the front sealing gasket to realize the compression sealing of the cylindrical surface at the second end face of the low turbine shaft;
a vent hole at the second end surface of the low turbine shaft and a plug in interference fit with the rear fourth end surface of the oil collecting ring are arranged;
the rear baffle plate is provided with an air bleed hole, an oil inlet hole and an oil bleed hole, the air bleed hole is used for providing a passage for air outflow in the oil injection process of the sealed cavity, the oil inlet hole is used for providing an oil supply interface for the flow seal tester, and the oil bleed hole is used for realizing lubricating oil discharge and recovery in the sealed cavity after the sealing inspection is finished.
In a preferred embodiment of the present application, the plug is disposed within a sealed chamber, and the plug is pressed by pressure within the chamber.
In a preferred embodiment of the present application, the air bleed hole is provided above the tailgate in a vertical direction, the oil bleed hole is provided below the tailgate in the vertical direction, and the oil inlet hole is deflected by a predetermined angle with the air bleed hole.
In a preferred embodiment of the present application, the front sealing cover includes a first semicircle and a second semicircle that are separated from each other, and the first semicircle and the second semicircle are fixedly connected by a connecting member.
In a preferred embodiment of the present application, the rear baffle and the rear end cover are fixed together by bolts.
In a preferred embodiment of the present application, the sealing performance inspection apparatus further includes a handle fixedly disposed on the tailgate.
In a preferred embodiment of the present application, the front sealing cover and the front sealing gasket are in a wedge-shaped interference fit.
In a preferred embodiment of the application, the pull rod is provided with an axial positioning structure, and the minimum axial distance between the front end cover and the rear end cover is limited by controlling the axial dimension of the axial positioning structure, so that the thin-wall part is prevented from being deformed under pressure.
The device for checking the tightness of the transition bearing cavity of the engine can meet the requirement of the air tightness sealing of the bearing cavity and cannot damage thin-walled parts in a low-pressure turbine rotor assembly.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of transition bearing seal cavity formation.
Fig. 2a is a front end side view of the seal inspection apparatus of the present application.
Fig. 2b is a rear end side view of the seal inspection apparatus of the present application.
Fig. 3 is a schematic view of the seal inspection apparatus of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to overcome the following technical problems in the prior art:
1) the front fulcrum sealing cavity is an annular cavity, the outer ring cylindrical surface is of a honeycomb hole-shaped structure, the end surface width is narrow, the inner ring is a smooth outer arc surface, the sealing difficulty is high, and the sealing reliability needs to be ensured;
2) the end face of the rear fulcrum runway 13 is a narrower small end face structure (the width is less than 1mm), and the problem of high sealing difficulty is also faced;
3) the structure at the sealing position is mostly a thin-wall part, and the deformation is easy to generate after the stress;
4) the sealing device needs to have operability so as to ensure that the actual use process is convenient and simple and the working efficiency is high.
Therefore, the application provides an engine transition bearing cavity tightness checking device. As shown in fig. 2a and 2b, the sealing performance inspection apparatus 4 of the present application mainly includes a front baffle 41, a front sealing cover 42, a front baffle sealing pad 451, a front sealing pad 452, a rear baffle 43, a rear end cover 48, a pull rod 44, a plug 47, and the like, and establishes a sealing cavity on the low-vortex rotor assembly by using the flange joint gasket sealing principle.
As shown in fig. 3, the front baffle 41 and the front sealing cover 42 are connected by bolts to form a front baffle assembly, the rear baffle 43 and the rear end cover 48 are fixed by bolts to form a rear baffle assembly, the pull rod 44 passes through a connecting bolt hole formed in the low-speed scroll shaft 1, and compression nuts are arranged at two ends of the pull rod, so that the front baffle assembly and the rear baffle assembly can be fixed on the low-speed scroll rotor assembly by tightening the nuts, and the positions of the first end face K1 and the rear end face K5 are sealed by the front baffle sealing gasket 451. The front sealing cover 42 is fixed on the front baffle 41 by means of bolts and is provided with a horizontal longitudinal mounting edge 421, the front sealing gasket 452 is arranged in the horizontal longitudinal mounting edge 421, the horizontal longitudinal mounting edge 421 forms a bolt pressing structure for connecting the front sealing cover 42 with the front baffle 41, and the bolt pressing structure is superposed with interference fit between the front sealing cover 42 and the front sealing gasket 452 to enable the front sealing gasket 452 to press and seal the position of the low-pressure turbine shaft body cylindrical surface K2. A small interference fit plug 47 is arranged at the position of the vent hole step end face K3 on the low-pressure turbine shaft and the position of the oil-collecting ring rear end face K4. The rear baffle 43 is provided with an air bleed hole 461, an oil inlet hole 462 and an oil bleed hole 463, the air bleed hole 461 is used for providing a passage for air flowing out in the oil injection process of the sealed cavity, the oil inlet hole 462 is used for providing an oil supply interface for the flow seal tester, and the oil bleed hole 463 is used for realizing the discharge and recovery of lubricating oil in the cavity after the sealing inspection is finished.
In the present application, the plug 47 is disposed in a sealing cavity formed by the tightness inspection device, and the pressure in the sealing cavity generates a pressing force on the plug 47 at the corresponding position, so that the plug can exert a better sealing effect.
In this application, the bleed hole 461 is located directly above the vertical position on the tailgate 43, the oil inlet hole 462 is circumferentially deflected by a certain angle from the bleed hole 461 directly above, and the bleed hole 463 is located directly below the tailgate 43, so that clean discharge of the lubricating oil can be realized.
Referring to fig. 2a, if the front sealing cover 42 adopts a conventional full-ring structure, during installation, the front sealing cover needs to be sleeved in from a front shaft head of the low-pressure turbine shaft 1 and then moves axially to a far left and right distance to reach an assembly position, during which the concentricity of the front sealing cover 42 and the low-pressure turbine shaft 1 needs to be controlled very well, otherwise, the front sealing cover is difficult to move and collides with a machine part, and the like, so that for the safety of the machine part, the front sealing cover 42 is made into a split two-half-circular structure, before use, the two-half-circular structure is respectively installed on the front baffle plate 41, and then the two-half-circular structure is fixedly pressed on the low-pressure turbine shaft 1 by using a bolt of a horizontal longitudinal installation edge. The two semicircular structures are provided with large compression surfaces, the compression surfaces are matched through a threaded piece for use, the half-and-half longitudinal installation edges are fixed, the effective compression area is increased, and the sealing state of the butt joint surfaces is ensured.
Referring to FIG. 3, the front seal 452 and front seal cap 42 of the present application are shown in a wedge-shaped interference fit configuration. As the fastening bolts on front seal cover 42 are tightened, the compression of front seal 452 against low-pressure turbine shaft cylindrical surface K2 is thereby increased in accordance with the principle of the wedge action. Meanwhile, the deformation force generated by the large interference fit of the seam allowance between the front sealing cover 42 and the front sealing gasket 451 is transmitted to the low-pressure turbine shaft cylindrical surface K2 through the elastic sealing gasket, so that the sealing effect is further enhanced, and the sealing performance is ensured.
A groove is formed in the corresponding position of the rear baffle 43, a rear sealing gasket 431 is arranged in the groove, the rear sealing gasket 431 is tightly pressed with the rear end face K5 of the fulcrum runway to realize sealing, the rear end face of the five-fulcrum runway is narrow, the rear sealing gasket 431 is easily cut into the rear sealing gasket 431 in the installation process of the tightness inspection device, and when the rear end face of the five-fulcrum runway is cut into the rear sealing gasket 431 too deeply, the rear sealing gasket 431 is pushed to the rear baffle to easily cause structural damage; in addition, when the compression nuts at the two ends of the pull rod 44 are tightened, the front and rear baffles of the device generate pressure on the disk center sealing assembly and the five-fulcrum runway, and the possibility of compression deformation exists because the two components are thin-walled components. Therefore, the axial distance between the front baffle and the rear baffle needs to be controlled to the minimum value, in the application, the axial positioning mechanism is designed on the pull rod, the positioning axial size of the mechanism is strictly regulated by constructing an assembly size chain under the condition of considering the compression amount of the sealing gasket, and different groups of adjusting gaskets are matched to adapt to factors such as machining deviation, deformation and the like of a machine part, so that the reliable axial positioning of the front baffle and the rear baffle under the actual application working condition is finally ensured.
Finally, the leakproofness inspection device of this application still includes handle 49, and handle 49 is fixed to be set up on backplate 43, can make things convenient for operating personnel to install the backplate subassembly.
The device for checking the sealing performance of the transition bearing cavity of the engine has the following advantages:
1) in order to prevent the damage of the five-fulcrum runway cutting-in sealing gasket to the rear baffle plate and the compression deformation of the five-fulcrum runway and the four-fulcrum bearing seat in the process of axially and tightly sealing the end faces of the four-fulcrum bearing seat and the five-fulcrum runway, an assembly dimension chain is constructed, the axial distance between the front baffle plate and the rear baffle plate under the condition of considering the compression amount of the sealing gasket is obtained, an axial positioning section is designed on a pull rod, the axial dimension is strictly regulated according to the calculated distance, and a group adjusting pad is arranged for ensuring the adaptability to the actual deviation influence of a machine part, so that the aims of axially and safely compressing and positioning the tool are finally fulfilled;
2) due to structural limitation, the position of the cylindrical surface of the low-pressure turbine shaft is required to establish a sealing surface. The shape of the low-pressure turbine shaft cylindrical surface is difficult to seal, the front sealing gasket is tightly pressed on the low-pressure turbine shaft cylindrical surface by adopting a bolt structure at the horizontal longitudinal installation edge, a seam allowance between the front sealing gasket and the front sealing gasket is designed to be large interference fit, deformation force generated by the interference fit is transmitted to the low-pressure turbine shaft cylindrical surface, the pressing sealing effect of the sealing gasket is enhanced, and the integral sealing performance is ensured;
3) because the front end of the low-pressure turbine shaft is far away from the position of the sealing cavity, the front end of the low-pressure turbine shaft is required to be sleeved in from the shaft sleeve by adopting the conventional whole-ring end cover design, and the problems of difficult installation and easy damage to machine parts exist, the front sealing cover is designed into a two-half structure, and the operability and the safety of the machine parts are improved; meanwhile, the large-pressing-surface threaded part is designed to serve as two half longitudinal mounting edge fastening pieces, so that the effective pressing area is increased, and the sealing state of the butt joint surface is ensured.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. An engine transition bearing cavity tightness inspection device, characterized in that the tightness inspection device (4) comprises:
a front baffle plate assembly formed by connecting a front baffle plate (41) and a front sealing cover (42) through a connecting piece, a rear baffle plate assembly formed by fixedly connecting a rear baffle plate (43) and a rear end cover (48), and a pull rod (44);
the pull rod (44) penetrates through a low-pressure turbine shaft (1) connecting bolt hole and fixes the front baffle plate assembly and the rear baffle plate assembly on the low-pressure turbine rotor assembly through a compression nut, so that the positions of the front end face (K1) of the low-pressure turbine rotor assembly and the rear end face (K5) of the rear fulcrum runway are sealed;
the front sealing cover (42) is provided with a horizontal longitudinal mounting edge (421), a front sealing gasket (452) is arranged in the horizontal longitudinal mounting edge (421), the horizontal longitudinal mounting edge (421) forms a bolt pressing structure for connecting with the front baffle (41), and the bolt pressing structure is superposed with a wedge-shaped interference fit between the front sealing cover (42) and the front sealing gasket (452) to realize cylindrical surface pressing sealing at the second end face (K2) of the low turbine shaft;
a plug (47) in interference fit is arranged at the position of the vent hole at the step end face (K3) of the shaft body vent hole of the low turbine shaft and the position of the rear end face (K4) of the oil collecting ring;
an air bleed hole (461), an oil inlet hole (462) and an oil bleed hole (463) are formed in the rear baffle plate (43), the air bleed hole (461) is used for providing a channel for air outflow in the oil injection process of the sealing cavity, the oil inlet hole (462) is used for providing an oil supply interface for the flow sealing tester, and the oil bleed hole (463) is used for achieving lubricating oil discharge and recovery in the cavity after the sealing inspection is completed.
2. The engine transition bearing cavity tightness inspection device according to claim 1, characterized in that said plug (47) is disposed in a seal cavity, said plug being caused to generate a pressing force by a cavity internal pressure.
3. The engine transition bearing cavity tightness inspection device according to claim 1, wherein said gas release hole (461) is vertically disposed above said tailgate (43), said oil release hole (463) is vertically disposed below said tailgate (43), and said oil inlet hole (462) is deflected by a predetermined angle with respect to said gas release hole (461).
4. The engine transition bearing cavity tightness inspection device according to claim 1, characterized in that the front sealing cover (42) comprises a first semicircle and a second semicircle that are separated from each other, and the first semicircle and the second semicircle are fixedly connected by a connecting piece.
5. The engine transition bearing cavity tightness inspection device according to claim 1, characterized in that said rear baffle (43) and said rear end cover (48) are fixed as one body by bolts.
6. The engine transition bearing cavity tightness inspection device according to claim 1, characterized in that said tightness inspection device further comprises a handle (49), said handle (49) being fixedly disposed on the tailgate (43).
7. The engine transition bearing cavity tightness inspection device according to claim 1, characterized in that a wedge-shaped interference fit is provided between the front sealing cover (42) and the front sealing gasket (452).
8. The engine transition bearing cavity tightness inspection device according to claim 1, characterized in that the pull rod (44) is provided with an axial positioning structure, and the minimum axial distance between the front end cover and the rear end cover is limited by controlling the axial dimension of the axial positioning structure, so as to ensure that the thin-wall part is not deformed under pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010555806.2A CN111678646B (en) | 2020-06-17 | 2020-06-17 | Engine transition bearing cavity tightness inspection device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010555806.2A CN111678646B (en) | 2020-06-17 | 2020-06-17 | Engine transition bearing cavity tightness inspection device |
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| CN111678646A CN111678646A (en) | 2020-09-18 |
| CN111678646B true CN111678646B (en) | 2022-04-01 |
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