CN109026394B - thermal protection structure deformation compensation method and thermal protection device - Google Patents
thermal protection structure deformation compensation method and thermal protection device Download PDFInfo
- Publication number
- CN109026394B CN109026394B CN201810598817.1A CN201810598817A CN109026394B CN 109026394 B CN109026394 B CN 109026394B CN 201810598817 A CN201810598817 A CN 201810598817A CN 109026394 B CN109026394 B CN 109026394B
- Authority
- CN
- China
- Prior art keywords
- cover plate
- engine
- nut
- air inlet
- support plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/24—Heat or noise insulation
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Plates (AREA)
Abstract
The invention provides a deformation compensation method and a thermal protection device for a thermal protection structure, wherein the method comprises the following steps: selecting a process cover plate with an operation hole, wherein the overall structural shape of the process cover plate and the position and the shape of a screw mounting hole are the same as those of a formal high-temperature alloy cover plate; the process cover plate and the positioning support plate nut are positioned and installed at a proper position of an engine air inlet channel; coating normal-temperature AB glue at the joint position of the positioning support plate nut and the engine air inlet channel and curing; and (4) removing the process cover plate, and fixedly mounting the formal high-temperature alloy cover plate on the air inlet channel of the engine. By applying the technical scheme of the invention, the technical problem of unmatched deformation caused by temperature difference between the thermal protection cover plate and the engine air inlet in the prior art is solved.
Description
Technical Field
The invention relates to the technical field of cover plate type thermal protection structures, in particular to a thermal protection structure deformation compensation method and a thermal protection device.
Background
because hypersonic aircraft flight mach number is high, and the surface aerodynamic thermal environment is abominable, installs apron on the engine intake duct and bears the vibration load that the engine brought on the one hand, and on the other hand bears the aerodynamic heating and the dynamic pressure load that the outflow brought, and the load environment is complicated, for solving the intake duct side dimension shape, intake duct structure thermal protection and the deformation coordination problem between intake duct apron and the engine intake duct, adopted high temperature alloy apron formula thermal protection scheme.
for adapting to engine intake duct profile, the superalloy apron is special-shaped irregular curved surface, realize connecting through multiple spot and engine intake duct, and the engine intake duct is engine function part, the configuration itself is complicated, the space that can be used to connect is limited, there is certain difference in temperature between engine intake duct side and its body, and the relative slip function that great difference in temperature leads to between apron and the intake duct structure is hardly realized to current apron formula heat protection structure, when the difference in temperature is great, can lead to warping between heat protection apron and the engine intake duct and mismatch.
Disclosure of Invention
The invention provides a thermal protection structure deformation compensation method and a thermal protection device, which can solve the technical problem of unmatched deformation caused by temperature difference between a thermal protection cover plate and an engine air inlet in the prior art.
According to an aspect of the present invention, there is provided a thermal protection structure deformation compensation method, including: selecting a process cover plate with an operation hole, wherein the overall structural shape of the process cover plate and the position and the shape of a screw mounting hole are the same as those of a formal high-temperature alloy cover plate; the process cover plate and the positioning support plate nut are positioned and installed at a proper position of an engine air inlet channel; coating normal-temperature AB glue at the joint position of the positioning support plate nut and the engine air inlet channel and curing; and (4) removing the process cover plate, and fixedly mounting the formal high-temperature alloy cover plate on the air inlet channel of the engine.
Furthermore, the engine air inlet channel is provided with a first accommodating hole, a second accommodating hole and a third accommodating hole which are sequentially connected, and after the process cover plate is selected, the deformation compensation method for the thermal protection structure further comprises the following steps: the cushion block is arranged in a first accommodating hole of the engine air inlet, and a cotton felt is attached to one side of the engine air inlet.
Further, the screw mounting hole and the location layer board nut of trying on dress technology apron specifically include: and fixing the relative positions of the screw mounting holes of the process cover plate and the screw mounting holes on the engine air inlet channel, sequentially penetrating countersunk screws through the process cover plate, the cotton felt, the cushion block and the engine air inlet channel, placing the positioning support plate nut in the third accommodating hole, and positioning the position of the positioning support plate nut through the countersunk screws.
Further, the thickness of the normal-temperature AB glue coated at the joint position of the positioning support plate nut and the engine air inlet channel is 0.2 mm-0.5 mm.
Further, the cushion passes through red glue setting in the first accommodation hole of engine intake duct, and the cotton felt covers one side at the engine intake duct through red glue subsides.
According to another aspect of the invention, a thermal protector for an engine intake duct is provided, which is connected with the engine intake duct by using the thermal protection structure deformation compensation method.
further, the thermal protection device comprises: the cushion block is arranged in a first accommodating hole of an engine air inlet; the cotton felt is attached to one side of the engine air inlet; the positioning support plate nut is positioned in the third accommodating hole and comprises a nut and a support plate, the nut is fixedly arranged on one side of the support plate, and the other side of the support plate is connected with an engine air inlet channel through normal-temperature AB glue; the high-temperature alloy cover plate is arranged on one side of the engine air inlet and is positioned on the cotton felt; the countersunk head screw penetrates through the high-temperature alloy cover plate, the cotton felt, the cushion block and the support plate of the positioning support plate nut in sequence and is matched with the thread section of the nut of the positioning support plate nut to realize the connection of the high-temperature alloy cover plate and the engine air inlet channel.
Further, a deformation compensation gap is formed between the supporting plate and the hole wall of the third accommodating hole.
Further, the deformation compensation gap is less than or equal to 2 mm.
Further, the countersunk-head screw includes a 90 ° countersunk-head screw or a 120 ° countersunk-head screw.
The technical scheme of the invention provides a deformation compensation method for a thermal protection structure, which realizes the fixation of a positioning support plate nut and the installation of a high-temperature alloy cover plate by positioning in a trial assembly stage and matching with normal-temperature AB glue, and realizes the sliding between the positioning support plate nut and an engine air inlet channel by utilizing the characteristic that the AB glue in a high-temperature state fails, thereby realizing the deformation compensation between the high-temperature alloy cover plate and an installation plane of the engine air inlet channel in a pneumatic heating state, and realizing the installation of the high-temperature alloy cover plate in a narrow space and the deformation compensation requirement of the high-temperature alloy cover plate in the pneumatic heating state. The method ensures the reliable connection of the high-temperature alloy cover plate and the engine air inlet channel body structure in a narrow space, solves the problem of deformation mismatching of the high-temperature alloy cover plate and the engine air inlet channel due to temperature difference, and realizes deformation compensation of the high-temperature alloy cover plate and the engine air inlet channel.
Drawings
the accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 illustrates a Z-direction cross-sectional view of a thermal shield apparatus provided in accordance with a particular embodiment of the present invention;
FIG. 2 illustrates an X-direction cross-sectional view of a thermal shield apparatus provided in accordance with a specific embodiment of the present invention;
FIG. 3 illustrates a schematic structural view of a positioning pallet nut provided in accordance with a specific embodiment of the present invention;
FIG. 4 illustrates a schematic structural diagram of a process cover plate provided in accordance with an embodiment of the present invention;
FIG. 5 illustrates a schematic structural diagram of a superalloy cover plate provided in accordance with an embodiment of the present invention.
Wherein the figures include the following reference numerals:
10. Cushion blocks; 20. a cotton felt; 30. positioning a splint nut; 31. a nut; 32. a support plate; 30a, a pallet first size; 30b, a pallet second size; 40. a high temperature alloy cover plate; 50. countersunk head screws; 60. a process cover plate; 100. an engine intake; 101. a mounting plane; 100a, an engine inlet first size; 100b, engine intake second size.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. 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. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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 is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 to 5, a thermal protection structure deformation compensation method according to an embodiment of the present invention includes: selecting a process cover plate 60 with an operation hole, wherein the overall structural shape of the process cover plate 60 and the position and the shape of a screw mounting hole are the same as those of a formal high-temperature alloy cover plate 40; the process cover plate 60 and the positioning supporting plate nut 30 are positioned and installed at a proper position of an engine air inlet channel by penetrating through an operation hole of the process cover plate 60, trial installing a screw installation hole of the process cover plate 60 and the positioning supporting plate nut 30; coating normal-temperature AB glue at the joint position of the positioning support plate nut 30 and the engine air inlet channel and curing; the process cover plate 60 is removed and the formal superalloy cover plate 40 is fixedly mounted on the engine intake.
By applying the configuration mode, the deformation compensation method for the thermal protection structure is provided, the method realizes the fixation of the positioning support plate nut and the installation of the high-temperature alloy cover plate by positioning in a trial assembly stage and matching with normal-temperature AB glue, and realizes the sliding between the positioning support plate nut and the engine air inlet channel by utilizing the characteristic that the AB glue in a high-temperature state fails, thereby realizing the deformation compensation between the high-temperature alloy cover plate and the installation plane of the engine air inlet channel in a pneumatic heating state, and realizing the installation of the high-temperature alloy cover plate in a narrow space and the deformation compensation requirement in the pneumatic heating state of the high-temperature alloy cover plate. The method ensures that the high-temperature alloy cover plate and the engine air inlet channel body are reliably connected in a narrow space, solves the problem that the high-temperature alloy cover plate and the engine air inlet channel are not matched in deformation caused by temperature difference, and realizes deformation compensation of the high-temperature alloy cover plate and the engine air inlet channel. The overall structural shape of the process cover plate and the positions and shapes of the screw mounting holes are the same as those of the formal superalloy cover plate, which means that the process cover plate 60 is different from the formal superalloy cover plate 40 only in that the process cover plate 60 has operation holes, and the other structures and shapes are the same as those of the formal superalloy cover plate 40.
Further, in the present invention, in order to enhance the heat protection effect on the engine intake duct, the engine intake duct has a first receiving hole, a second receiving hole, and a third receiving hole, which are connected in sequence, and after the selection of the process cover plate 60 is completed, the method for compensating for the deformation of the thermal protection structure further includes: the cushion block 10 is installed in a first receiving hole of an engine intake duct, and a cotton felt 20 is attached to one side of the engine intake duct.
In addition, in the present invention, the screw mounting hole of the trial-assembly process cover plate 60 and the positioning pallet nut 30 specifically include: and fixing the relative positions of the screw mounting holes of the process cover plate 60 and the screw mounting holes on the engine air inlet channel, sequentially penetrating countersunk screws 50 through the process cover plate 60, the cotton felt 20, the cushion block 10 and the engine air inlet channel, placing the positioning support plate nut 30 in a third accommodating hole, and positioning the position of the positioning support plate nut 30 through the countersunk screws 50.
By applying the configuration, the process cover plate 60 with the operation hole is firstly adopted for trial assembly, considering that the position of the positioning support plate nut 30 is a closed structure without operation conditions after the formal high-temperature alloy cover plate 40 is installed in place. Through the relative position fixing of the screw mounting hole of technology apron 60 and the screw mounting hole on the engine intake duct, pass technology apron 60, cotton felt 20, cushion 10 and engine intake duct 100 with countersunk screw 50 in proper order, place location layer board nut 30 in the third accommodation hole to fix a position the location layer board nut 30 through countersunk screw 50, this kind of mode can realize the accurate positioning to location layer board nut 30. On this basis, when the superalloy cover plate 40 needs to be formally installed, the positioning pallet nut 30 can be accurately aligned under the blind operation, and the positioning pallet nut 30 does not fall off in the installation process.
further, in the invention, in order to effectively solve the problem of deformation mismatch caused by temperature difference between the high-temperature alloy thermal protection cover plate and the engine air inlet channel, the thickness of the normal-temperature AB glue coated at the joint position of the positioning support plate nut 30 and the engine air inlet channel is 0.2mm to 0.5 mm. The sliding between the positioning support plate nut 30 and the engine air inlet channel structure is realized by utilizing the characteristic that the AB glue fails at the normal temperature in a high-temperature state, so that the deformation compensation between the cover plate structure and the installation plane of the engine air inlet channel structure in a pneumatic heating state is realized, and the requirements of the installation of the cover plate structure in a narrow space and the deformation compensation in the cover plate pneumatic heating state are met.
further, in the present invention, in order to effectively achieve heat conduction, the mat 10 may be configured to be disposed in the first receiving hole of the engine intake duct 100 by red glue, and the cotton felt 20 may be attached to one side of the engine intake duct 100 by red glue.
According to another aspect of the present invention, a thermal protector for an engine intake is provided, which is connected to an engine intake 100 using a thermal protection structure deformation compensation method as described above. Because the deformation compensation method of the thermal protection structure can realize the installation of the high-temperature alloy cover plate structure in a narrow space and the deformation compensation requirement of the cover plate in a pneumatic heating state, the thermal protection device is arranged on the engine air inlet 100 by utilizing the deformation compensation method of the thermal protection structure, the thermal protection performance of the engine air inlet 100 can be well improved, and the deformation coordination problem between the thermal protection device and the engine air inlet 100 can be solved.
Further, in the present invention, as shown in fig. 1 to 3, the thermal protection device includes a cushion block 10, a cotton felt 20, a positioning support plate nut 30, a high temperature alloy cover plate 40 and a countersunk screw 50, the cushion block 10 is disposed in a first receiving hole of the engine intake duct, the cotton felt 20 is attached to one side of the engine intake duct, the positioning support plate nut 30 is disposed in a third receiving hole, the positioning support plate nut 30 includes a nut 31 and a support plate 32, the nut 31 is fixedly disposed on one side of the support plate 32, the other side of the support plate 32 is connected to the engine intake duct 100 through a normal temperature AB glue, the high temperature alloy cover plate 40 is disposed on one side of the engine intake duct 100 and is disposed on the cotton felt 20, the countersunk head screw 50 sequentially penetrates through the high-temperature alloy cover plate 40, the cotton felt 20, the cushion block 10 and the supporting plate and is matched with the thread section of the nut of the positioning supporting plate nut 30 to realize the connection of the high-temperature alloy cover plate 40 and the engine air inlet 100.
By applying the configuration mode, the high-temperature alloy cover plate 40 is positioned at the outer side of the engine air inlet 100, and the high-temperature alloy cover plate 40 has the structural characteristics of special-shaped cambered surface and narrow space multipoint connection, so that the functions of bearing, maintaining shape and heat resistance can be realized. In addition, because the other side of layer board 32 is glued through normal atmospheric temperature AB and is connected with engine intake duct 100, consequently utilize the characteristic that the high temperature state AB glue became invalid, can realize the slip between positioning layer board nut structure and the engine intake duct 100 to realize under the pneumatic heating state of superalloy cover plate 40 and the deformation compensation between the engine intake duct structure mounting plane, realized under the narrow and small space the deformation compensation requirement under the installation of apron structure and the apron pneumatic heating state.
Specifically, as shown in fig. 4 and 5, the third receiving hole is a rectangular receiving hole, and the carrier plate in which the carrier plate nut 30 is positioned is a rectangular plate. When the positioning support plate nut 30 is assembled with the engine inlet duct 100, the other side of the support plate 32 is attached to the mounting plane 101 of the engine inlet duct 100 through normal temperature AB glue. As an embodiment of the present invention, as shown in fig. 2 and 3, the first dimension of the support plate is 22mm, the second dimension of the support plate is 14mm, the first dimension 100a of the engine inlet duct is 20mm, the second dimension 100b of the engine inlet duct is 30mm, the support plate 32 is placed in the third receiving hole of the engine inlet duct, and a deformation compensation clearance is provided between the support plate 32 and the hole wall of the third receiving hole. Considering the processing and manufacturing reasons and the existence of fillets at the matching positions of the two, the matching of the two can realize the deformation compensation of the high-temperature alloy cover plate 40 and the installation plane 101 of the engine inlet 100 in the local coordinate X direction and the Z direction relative to the original direction by not more than 2 mm.
Further, in the present invention, in order to achieve the connection between the superalloy cover plate and the engine intake duct 100, the countersunk screw 50 may be configured to include a 90 ° countersunk screw or a 120 ° countersunk screw. In view of the firmness and load-bearing characteristics of the connection, a 90 ° countersunk head screw is preferred as a connection between the superalloy cover plate and the engine inlet 100.
For further understanding of the present invention, the following describes the process of connecting the thermal protection device to the engine intake duct by using the deformation compensation method of the thermal protection structure of the present invention with reference to fig. 1 to 5.
As shown in fig. 1 and 5, the thermal protection device comprises a cushion block 10, a cotton felt 20, a positioning support plate nut 30, a high-temperature alloy cover plate 40 and a countersunk screw 50, the positioning support plate nut 30 comprises a nut 31 and a support plate 32, the nut 31 is fixedly arranged on one side of the support plate 32, the nut 31 and the support plate 32 are integrally formed, the quartz cushion block is adopted as the cushion block 10, an engine air inlet channel is provided with a first accommodating hole, a second accommodating hole and a third accommodating hole which are sequentially connected, the high-temperature alloy cover plate 40 has the structural characteristics of a special-shaped arc surface and narrow space multipoint connection, and the functions of bearing, shape maintenance and heat prevention can be realized.
When assembling the thermal protection device and the engine inlet duct 100, firstly, red glue with the thickness of 0.2mm to 0.3mm is coated on the bottom surface of the quartz cushion block and is installed in the first accommodating hole of the engine inlet duct 100. Next, a circle of the cotton felt 20 was coated with red glue and mounted on one side of the engine intake duct 100. After the formal part is installed in place, the position of the positioning support plate nut 30 is a closed structure and has no operating condition, so a process cover plate 60 needs to be adopted for trial assembly, the process cover plate 60 is different from the high-temperature alloy cover plate 40 only in that the process cover plate 60 is provided with an operating hole, and the overall structural shape of the process cover plate 60 and the position and the shape of a screw installation hole are the same as those of the formal high-temperature alloy cover plate 40.
The screw mounting holes on the process cover plate 60 and the screw mounting holes on the engine inlet channel 100 are fixed in relative positions, the countersunk screws 50 sequentially penetrate through the process cover plate 60, the cotton felt 20, the cushion block 10 and the second accommodating hole and the third accommodating hole of the engine inlet channel, the positioning support plate nuts 30 are placed in the third accommodating holes, the positions of the positioning support plate nuts 30 are positioned through the countersunk screws 50, and then the high-temperature alloy 90-degree countersunk screws 50 are mounted. And then, coating normal-temperature AB glue with the thickness of 0.2-0.5 mm on the joint position of the positioning support plate nut 30 and the engine air inlet channel 100, namely one circle of the support plate of the positioning support plate nut 30, wiping off redundant glue by using cotton cloth, and curing for 1-2 hours. And finally, removing the high-temperature alloy 90-degree countersunk head screw 50, detaching the technical cover plate 60, ensuring the positions of the cushion block 10 and the cotton felt 20 to be unchanged, replacing the formal high-temperature alloy cover plate 40, and installing in place.
in the present embodiment, the first dimension of the support plate is 22mm, the second dimension of the support plate is 14mm, the first dimension 100a of the engine inlet duct is 20mm, the second dimension 100b of the engine inlet duct is 30mm, the support plate 32 is placed in the third receiving hole of the engine inlet duct, and a deformation compensation gap is formed between the support plate 32 and the hole wall of the third receiving hole. Considering the processing and manufacturing reasons and the existence of fillets at the matching positions of the two, the matching of the two can realize the deformation compensation of the high-temperature alloy cover plate 40 and the installation plane 101 of the engine inlet 100 in the local coordinate X direction and the Z direction relative to the original direction by not more than 2 mm.
The screw for connecting the high-temperature alloy cover plate 40 and the positioning support plate nut 30 is a 90-degree countersunk screw 50, so that the screws for connecting the high-temperature alloy cover plate 40, the 90-degree countersunk screw 50 and the positioning support plate nut 30 can slide on the installation plane 101 of the engine air inlet 100 as a whole, and the sliding directions are the local coordinate X direction and the local coordinate Z direction of the installation plane 101 of the engine air inlet 100. Alternatively, as another embodiment of the present invention, a 120 ° countersunk head screw 50 may be used as a connecting member between the superalloy cover plate 40 and the retainer plate nut 30.
Through above structure and operation, can realize in the narrow and small space high temperature alloy apron and the engine intake duct structure reliably be connected, solve high temperature alloy apron and engine intake duct because the deformation that the difference in temperature brought mismatch the problem, realize the deformation compensation of the two.
spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. the utility model provides a thermal protection structure deformation compensation method, engine intake duct have the first accommodation hole, second accommodation hole and the third accommodation hole that connect gradually, its characterized in that, thermal protection structure deformation compensation method includes:
Selecting a process cover plate with an operation hole, wherein the overall structure shape of the process cover plate and the position and the shape of a screw mounting hole are the same as those of a formal high-temperature alloy cover plate (40);
Installing a cushion block (10) in a first accommodating hole of an engine air inlet, and attaching a cotton felt (20) to one side of the engine air inlet;
The positioning support plate nut (30) is placed in the third accommodating hole, the positioning support plate nut (30) is positioned through the countersunk head screw (50), and the process cover plate and the positioning support plate nut (30) are positioned and installed at a proper position of the engine inlet channel;
coating normal-temperature AB glue at the joint position of the positioning support plate nut (30) and the engine air inlet channel and curing;
And (3) removing the process cover plate, and fixedly mounting a formal high-temperature alloy cover plate (40) on the engine air inlet.
2. the deformation compensation method for the thermal protection structure according to claim 1, wherein the thickness of the normal temperature AB glue coated at the joint position of the positioning support plate nut (30) and the engine inlet channel is 0.2mm to 0.5 mm.
3. The method for compensating deformation of a thermal protection structure according to claim 1 or 2, wherein the cushion block (10) is arranged in the first accommodating hole of the engine air inlet channel through red glue, and the cotton felt (20) is attached to one side of the engine air inlet channel through the red glue.
4. A thermal protector for an engine inlet, characterized in that it is connected to an engine inlet using the thermal protection structure deformation compensation method according to any one of claims 1 to 3.
5. The heat shield for an engine intake according to claim 4, comprising:
the cushion block (10), the cushion block (10) is arranged in a first accommodating hole of an engine air inlet;
The cotton felt (20) is attached to one side of the air inlet channel of the engine;
The positioning support plate nut (30), the positioning support plate nut (30) is located in the third containing hole, the positioning support plate nut (30) comprises a nut (31) and a support plate (32), the nut (31) is fixedly arranged on one side of the support plate (32), and the other side of the support plate (32) is connected with an engine air inlet channel through normal-temperature AB glue;
The high-temperature alloy cover plate (40), the high-temperature alloy cover plate (40) is arranged on one side of an engine air inlet and is positioned on the cotton felt (20);
Countersunk screw (50), countersunk screw (50) pass in proper order superalloy cover plate (40), cotton felt (20), cushion (10) and the layer board of location layer board nut (30) and with the nut of location layer board nut (30) cooperatees in order to realize being connected of superalloy cover plate (40) and engine intake duct.
6. The heat shield for an engine inlet duct according to claim 5, characterized in that the carrier plate (32) has a deformation-compensating clearance with the bore wall of the third receiving bore.
7. The heat shield for an engine intake according to claim 6, wherein the deformation compensating clearance is less than or equal to 2 mm.
8. The heat shield for an engine intake duct according to claim 5, characterized in that the countersunk-head screw (50) comprises a 90 ° countersunk-head screw or a 120 ° countersunk-head screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810598817.1A CN109026394B (en) | 2018-06-12 | 2018-06-12 | thermal protection structure deformation compensation method and thermal protection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810598817.1A CN109026394B (en) | 2018-06-12 | 2018-06-12 | thermal protection structure deformation compensation method and thermal protection device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109026394A CN109026394A (en) | 2018-12-18 |
| CN109026394B true CN109026394B (en) | 2019-12-13 |
Family
ID=64612611
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810598817.1A Active CN109026394B (en) | 2018-06-12 | 2018-06-12 | thermal protection structure deformation compensation method and thermal protection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109026394B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114046212B (en) * | 2021-11-30 | 2023-06-27 | 西安航天动力研究所 | Composite heat insulation structure with thermal deformation compensation function |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202147847U (en) * | 2010-11-25 | 2012-02-22 | 北京空间技术研制试验中心 | Device for mounting large diameter thin wall structure on spacecraft |
| CN103062508A (en) * | 2011-10-24 | 2013-04-24 | 中国航空工业集团公司沈阳发动机设计研究所 | Abnormal-shaped nut type floating sealing structure used for penetrating through cartridge receiver |
| CN204512660U (en) * | 2015-02-25 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of aeroengine has the pipe-support structure that in-plane displancement compensates |
| CN105319047B (en) * | 2015-10-20 | 2018-10-26 | 四川成发航空科技股份有限公司 | Aero-engine casing is through-flow stomata flow testing device |
-
2018
- 2018-06-12 CN CN201810598817.1A patent/CN109026394B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109026394A (en) | 2018-12-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20140332640A1 (en) | System and method for mounting aircraft system components in the crown area of an aircraft | |
| CN104787299A (en) | Method for producing part of an aircraft fuselage and tool for implementing said method | |
| US8540191B2 (en) | Device for holding an insulating blanket and for fastening two-parts systems | |
| CN109026394B (en) | thermal protection structure deformation compensation method and thermal protection device | |
| CN108942327A (en) | It is a kind of for processing the fixture of technique for aircraft composite beam | |
| US8348209B2 (en) | Universal retaining device, particularly for fastening panel elements and/or accessory parts in aircraft | |
| US8890033B2 (en) | Bond line heating pad system | |
| CN105522497B (en) | A kind of aircraft skin, wallboard class part locating method for polytypic | |
| CN110228422B (en) | Car logo positioning and mounting method and auxiliary tool | |
| CN108834318A (en) | A kind of FPC localization tool | |
| US8047469B2 (en) | Airframe attachment fitting | |
| CN214373224U (en) | But angle regulation's vibration tool and OBU test structure | |
| CN213917814U (en) | Screw fast assembly frock | |
| US11077929B2 (en) | Pressure bulkhead system, pressure bulkhead assembly support tool, and method for assembling a pressure bulkhead system | |
| CN108789234B (en) | Method for assembling heating sheet on inclined plane | |
| CN202319814U (en) | Connecting structure for vehicle air conditioner duct | |
| CN208496803U (en) | Disassembly and assembly structure and test fixture | |
| CN106253161A (en) | A kind of composite material cable cover | |
| CN217412341U (en) | Clamping device and system | |
| CN109319090A (en) | A kind of installation method of embedded conformal antenna cover | |
| CN216217791U (en) | High-precision flexible printed board tool carrier | |
| CN219718850U (en) | Anti-surge anti-interference power panel | |
| CN211012889U (en) | Rear windshield glass positioning, assembling and detecting device | |
| CN215003490U (en) | Utensil is examined to static sealing strip environment of simulation car door | |
| CN212951191U (en) | Satellite is to ground expansion cabin strutting arrangement |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |