CN116928484A - Fire-proof structure for accessory case of aeroengine - Google Patents

Fire-proof structure for accessory case of aeroengine Download PDF

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Publication number
CN116928484A
CN116928484A CN202310746638.9A CN202310746638A CN116928484A CN 116928484 A CN116928484 A CN 116928484A CN 202310746638 A CN202310746638 A CN 202310746638A CN 116928484 A CN116928484 A CN 116928484A
Authority
CN
China
Prior art keywords
oil
elastic
cavity
groove
blanking cover
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.)
Pending
Application number
CN202310746638.9A
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Chinese (zh)
Inventor
王帅
罗敏
李超
宋双文
黄炎浩
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hunan Aviation Powerplant Research Institute AECC
Original Assignee
Hunan Aviation Powerplant Research Institute AECC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hunan Aviation Powerplant Research Institute AECC filed Critical Hunan Aviation Powerplant Research Institute AECC
Priority to CN202310746638.9A priority Critical patent/CN116928484A/en
Publication of CN116928484A publication Critical patent/CN116928484A/en
Pending legal-status Critical Current

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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
    • F02C7/06—Arrangements of bearings; Lubricating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K17/00—Safety valves; Equalising valves, e.g. pressure relief valves
    • F16K17/02—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side
    • F16K17/04—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side spring-loaded
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K17/00—Safety valves; Equalising valves, e.g. pressure relief valves
    • F16K17/02—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side
    • F16K17/164—Safety valves; Equalising valves, e.g. pressure relief valves opening on surplus pressure on one side; closing on insufficient pressure on one side and remaining closed after return of the normal pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K27/00—Construction of housing; Use of materials therefor
    • F16K27/02—Construction of housing; Use of materials therefor of lift valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L55/00—Devices or appurtenances for use in, or in connection with, pipes or pipe systems
    • F16L55/10—Means for stopping flow from or in pipes or hoses
    • F16L55/1026—Fire protection devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L55/00—Devices or appurtenances for use in, or in connection with, pipes or pipe systems
    • F16L55/10—Means for stopping flow from or in pipes or hoses
    • F16L55/11—Plugs

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Gasket Seals (AREA)

Abstract

The application discloses a fire-proof structure of an accessory case of an aeroengine, which comprises the following components: the device comprises a part needing fireproof design, an elastic blocking cover component playing a role in end blocking and a sealing component playing a role in sealing. An oil-sliding cavity and an oil outlet channel communicated with the oil-sliding cavity are arranged in the part to be fireproof, and the inner wall surface of the oil outlet channel is inwards concave at the position close to the oil-sliding cavity to form a limiting ring groove. After the elastic plug cover component is inserted into the oil-sliding cavity through the oil outlet channel, the elastic stop shoulder part at the outer end part of the elastic plug cover component is deformed and then clamped in the limiting ring groove, so that external flame is prevented from entering the oil-sliding cavity through a gap between the elastic stop shoulder and the limiting ring groove. The sealing component is arranged on the outer circle of the elastic blanking cover component and is positioned between the elastic blanking cover component and the lubricating oil cavity so as to seal a gap between the elastic blanking cover component and the lubricating oil cavity. The fireproof structure of the application is almost impossible to burn the sealing component positioned in the lubricating oil cavity, thereby playing a good role in protecting the sealing component, improving the lubricating oil sealing effect and reducing the test risk.

Description

Fire-proof structure for accessory case of aeroengine
Technical Field
The application relates to the field of fire prevention of an aircraft engine accessory case, in particular to a fire prevention structure of an aircraft engine accessory case.
Background
The design requirement of the aeroengine, especially the civil aeroengine, has strict fireproof requirement on parts, in the working process of the parts, the total amount of combustible liquid in the parts reaches more than 250ml and the like, the parts must pass a fireproof test, the test condition of the fireproof test is extremely strict, the ignition dangerous part in the parts needs to be oiled for 5 minutes according to the engine state at the high flame temperature of 1100 ℃, then the oil is not pumped for 10 minutes, and the parts are kept in the minimum oil quantity state of the engine, and in this state, the situation that oil leakage of the parts does not occur is regarded as passing the fireproof test.
Therefore, parts such as an oil tank, an accessory case, an oil filter case and the like in an engine are parts which are frequently required to be subjected to a fireproof test, and an excellent fireproof structure is adopted at the easy ignition point of the parts, so that the part has an important effect of improving the success rate of the fireproof test. The existing design method is mainly to increase the wall thickness or the oil quantity of the ignition point through adding a heat shield for heat dissipation:
1) The heat shield is added, so that the influence on important indexes of the engine is large, and space is not provided for all ignition dangerous points;
2) Increasing the wall thickness, on the one hand, has limited ability to increase fire resistance and also increases engine weight;
3) The oil flow near the ignition point is increased, so that the heat dissipation capacity can be increased, but the ignition risk is also brought, and if the case has metallurgical defects or tiny cracks, the case can cause strong fire on the horse, so that the test fails.
In addition, the existing lubricating oil tank is often of an integrated structure, so that the structure is complex, oil ways are numerous, and an oil supply and return system and a ventilation system of the lubricating oil tank are very complex in a fireproof test, so that poor oil supply and return matching of the oil supply and return system or unsmooth exhaust of the ventilation system easily occurs in the fireproof test. The aeroengine lubricating oil tank is formed by casting thin-wall aluminum magnesium alloy in consideration of weight reduction, the pressure resistance is limited (0.2-0.4 MPa), if the oil supply and return system is poor in oil supply and return matching or the ventilation system is unsmooth in exhaust in the test process, the lubricating oil tank is easy to burst, the lubricating oil is sprayed out, and big fire is caused, so that accidents are caused. The conventional pressure test instrument needs to be perforated on the lubricating oil tank, so that the risk of failure caused by oil leakage of the lubricating oil tank in the test process is increased, and on the other hand, the test equipment is generally difficult to withstand the high temperature of the fireproof test and is easy to fail.
Disclosure of Invention
The application provides a fire-proof structure of an accessory case of an aeroengine, which aims to solve the technical problems that the increasing of a heat shield in the existing fire-proof design method has great influence on important indexes of the engine, the increasing of the wall thickness is limited on one hand, the increasing of the fire-proof capacity is limited, the weight of the engine is increased, the oil flow near a firing point is increased, the heat dissipation capacity is increased on the other hand, but the firing risk is brought, and the test fails.
The technical scheme adopted by the application is as follows:
an aircraft engine accessory case fire protection structure comprising: the device comprises a part to be fireproof, an elastic blocking cover component for blocking an end part and a sealing component for sealing, wherein the part to be fireproof is required to be subjected to fireproof design; an oil sliding cavity and an oil outlet channel communicated with the oil sliding cavity are arranged in the part needing to be fireproof, and the inner wall surface of the oil outlet channel is inwards concave at the position close to the oil sliding cavity to form a limit ring groove; after the elastic plug cover assembly is inserted into the oil-sliding cavity through the oil outlet channel, the elastic retaining shoulder part at the outer end part of the elastic plug cover assembly deforms and is clamped in the limiting ring groove, so that external flame is prevented from entering the oil-sliding cavity through a gap between the elastic retaining shoulder and the limiting ring groove; the sealing component is arranged on the outer circle of the elastic blanking cover component and is positioned between the elastic blanking cover component and the lubricating oil cavity so as to seal a gap between the elastic blanking cover component and the lubricating oil cavity.
Further, the sealing assembly comprises a plurality of sealing rings which are sequentially arranged at intervals along the axial direction of the elastic blanking cover assembly; the outer circular surface of the elastic blanking cover component is correspondingly provided with a plurality of mounting ring grooves for mounting a plurality of sealing rings one by one, and the sealing rings are mounted in the correspondingly arranged mounting ring grooves; the wall thickness c between two adjacent mounting ring grooves is more than or equal to 1.5mm.
Further, the circumferential chamfer at the joint of the inner side edge of the limit ring groove and the oil slide cavity forms a guide conical surface; the axial distance b between the conical bottom of the guide conical surface and the nearest mounting ring groove is more than or equal to 1.5mm.
Further, the elastic blanking cover assembly comprises an installation blanking cover and an elastic check ring; the mounting blanking cover comprises a blanking cover shaft body and a limiting stop shoulder which are sequentially arranged along the axial direction and connected, the limiting stop shoulder is limited in a limiting ring groove after the blanking cover shaft body is inserted into the oil sliding cavity through the oil outlet channel, and the sealing assembly is arranged on the outer circle of the blanking cover shaft body; the elastic retainer ring is clamped in the limiting ring groove after being deformed, is positioned at the outer side of the installation blanking cover and is tightly connected with the installation blanking cover to form an elastic retaining shoulder.
Further, the limit ring groove comprises a first limit groove and a second limit groove which are sequentially arranged along the axial direction and communicated with each other; the elastic retainer ring is clamped in the first limit groove; the limiting stop shoulder is positioned in the second limiting groove and abuts against the elastic retainer ring after extending along the axial direction, so that the two sides of the limiting stop shoulder are respectively clung to the inner side face of the second limiting groove and the inner side face of the elastic retainer ring under the action of the elastic retainer ring, and the outer side face of the elastic retainer ring is clung to the outer side face of the first limiting groove.
Further, the width f of the second limit groove along the axial direction is more than or equal to 2.5mm; the thickness e of the limiting stop shoulder along the axial direction is more than or equal to f+0.1mm; the radial height a of the limiting stop shoulder is more than or equal to 3mm; the radial distance d between the inner ring surface of the elastic retainer ring and the inner ring surface of the oil outlet channel is more than or equal to 3mm.
Further, the outer side surface of the first limit groove is an inclined groove surface gradually inclined from the groove bottom to the outer side; the outer side surface of the elastic retainer ring is an inclined ring surface matched with the inclined groove surface of the first limit groove.
Further, an oil inlet channel axially communicated with the oil sliding cavity is arranged in the part needing to be fireproof, and the oil inlet end of the oil inlet channel is communicated with the oil sliding tank; the aeroengine accessory case fireproof structure further comprises an elastic pressure relief assembly which is elastically arranged in the oil sliding cavity, the outer side end of the elastic pressure relief assembly is connected with an elastic blanking cover assembly, the opposite inner side end of the elastic pressure relief assembly is used for propping against an outlet of the oil inlet channel when the oil pressure in the oil sliding tank is normal, and the elastic pressure relief assembly is further used for axially shrinking after the oil pressure in the oil sliding tank exceeds the upper limit oil pressure so as to open the oil inlet channel for pressure relief.
Further, the inner side end of the plugging cover shaft body for installing the plugging cover is concavely extended to form a first installation cavity; the elastic pressure relief assembly comprises a mounting plug and a spring for supplying elastic force; the installation plug is concavely extended towards the outer side end of the installation plug cover to form a second installation cavity, the outer side end of the installation plug is axially inserted into the first installation cavity, and the opposite inner side end of the installation plug is used for propping against an outlet of the oil inlet channel; the spring is arranged in the second installation cavity, and two axial ends respectively prop against the cavity bottom of the first installation cavity and the cavity bottom of the second installation cavity to limit.
Further, let P be the restriction pressure of the oil tank, the compression of spring under the installed state is Deltax, the spring rigidity of spring is k, the internal diameter of oil feed passageway is g, the operational safety coefficient is 0.8, then the internal diameter g of oil feed passageway needs to satisfy the following relation:
the application has the following beneficial effects:
in order to solve the technical problems that the existing machine case and end cover are made of aluminum magnesium alloy materials and are easy to deform and warp in a high-temperature environment for a long time, and the screw is made of stainless steel and has different linear expansion coefficients, so that gaps are easily formed between the position, which is slightly far away from the screw, on the end cover and the machine case in the circumferential direction, of the end cover, and the machine case, so that lubricating oil leaks, in the fireproof structure, an end face sealing and fixing mode of the end cover and the screw is omitted, and a blocking and limiting mode of an elastic blocking cover component and a limiting ring groove is adopted, wherein in the blocking and limiting mode, the main body part of the elastic blocking cover component is inserted into a lubricating oil cavity, the exposed elastic blocking shoulder part is clamped in the limiting ring groove for limiting, so that when the elastic blocking cover component is in the high-temperature environment for a long time, the elastic blocking cover component is difficult to deform and warp, the elastic blocking shoulder part is easy to deform, so that the gaps are difficult to occur on the end face of the machine case, the lubricating oil leaks, and parts are easy to pass the fireproof test; on the other hand, in the fireproof structure, the elastic blocking shoulder part of the elastic blocking cover assembly can be clamped in the limiting ring groove after being fractal changed, so that external flame can enter the lubricating oil cavity only through more than four corners from the outer ring and the inner ring of the elastic blocking shoulder, burning of the sealing assembly positioned in the lubricating oil cavity is almost impossible, the sealing assembly is well protected, the lubricating oil sealing effect is improved, and the test risk is reduced.
In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic front view of an aircraft engine accessory case fire protection structure in accordance with a preferred embodiment of the present application;
fig. 2 is a schematic dimensional view of an aircraft engine accessory case fire protection structure according to a preferred embodiment of the present application.
Description of the drawings
10. Fireproof parts are needed; 101. an oil-sliding cavity; 102. an oil outlet channel; 103. a limit ring groove; 104. a guide conical surface; 105. an oil inlet passage; 106. a pressure relief hole; 20. an elastic blanking cover assembly; 201. installing a ring groove; 21. installing a blanking cover; 211. a blanking cover shaft body; 212. limiting stop shoulders; 22. a circlip; 30. a seal assembly; 31. a seal ring; 40. an elastic pressure relief assembly; 41. installing a plug; 42. and (3) a spring.
Detailed Description
Embodiments of the application are described in detail below with reference to the attached drawing figures, but the application can be practiced in a number of different ways, as defined and covered below.
Referring to fig. 1, a preferred embodiment of the present application provides an aircraft engine accessory case fire protection structure comprising: a fire-proof part 10 to be fire-proof, an elastic plug cover component 20 for end sealing and a sealing component 30 for sealing. An oil-sliding cavity 101 and an oil outlet channel 102 communicated with the oil-sliding cavity 101 are arranged in the part 10 to be prevented from being corroded, and a limit ring groove 103 is formed in the inner wall surface of the oil outlet channel 102, which is close to the oil-sliding cavity 101, in a concave manner. After the elastic plug cover assembly 20 is inserted into the oil-sliding cavity 101 through the oil outlet channel 102, the elastic stop shoulder part at the outer end part of the elastic plug cover assembly is deformed and then clamped in the limit ring groove 103, so that external flame is prevented from entering the oil-sliding cavity 101 through a gap between the elastic stop shoulder and the limit ring groove 103. The sealing assembly 30 is disposed on the outer circle of the elastic plug assembly 20 and between the elastic plug assembly 20 and the oil chamber 101 to seal the gap therebetween.
In the prior art, an outlet of an oil-sliding cavity is generally subjected to end face sealing by adopting an end cover and an end face O-shaped sealing ring, or subjected to radial sealing by adopting an end cover and a radial single sealing ring, and the end cover and the casing are fixed by adopting a circle of screws arranged along the circumferential direction. In the end face sealing mode, flame is easy to burn an end face O-shaped ring through a small gap between the end cover and the casing, so that the O-shaped ring is damaged, and lubricating oil leakage is caused, and the test fails; in the radial sealing mode, a single O-shaped ring is adopted for radial sealing, and the heat resistance is slightly better than that of end face sealing, but the sealing is easy to lose efficacy even in a high-temperature environment for a long time, so that lubricating oil is leaked. Moreover, the casing and the end cover are generally made of aluminum-magnesium alloy materials, are in a high-temperature environment for a long time, and are easy to deform and warp, and because the screw is generally made of stainless steel, the linear expansion coefficients of the two materials are different, so that gaps are easily formed between the casing and the position, which is slightly far away from the screw, on the end cover in the circumferential direction, and the lubricating oil leakage is caused, so that the test fails.
The existing fireproof design thought mainly aims at preventing fireproof parts from being burnt through, so the fireproof design is mainly focused on the heat insulation design of the parts, but in the actual process, the deformation or failure of a sealing related structure is a more important factor for causing ignition of an engine, and the existing fireproof design just ignores the problem, so the existing sealing structure adopts several basic structures commonly used at present, and in the application, in order to solve the problem of lubricating oil leakage caused by the deformation or failure of the sealing related structure, the design of the fire protection structure of the aircraft engine accessory case is carried out, and the application is specifically as follows:
in order to solve the technical problems that the existing machine case and end cover are made of aluminum magnesium alloy materials and are easy to deform and warp in a high-temperature environment for a long time, and the screw is made of stainless steel, the linear expansion coefficients of the two materials are different, so that gaps are easily formed between the position, which is slightly far away from the screw, on the end cover and the machine case in the circumferential direction, of the end cover, so that lubricating oil leakage is caused; on the other hand, in the fireproof structure of the application, the elastic shoulder part of the elastic plug cover assembly 20 can be clamped in the limit ring groove 103 after being deformed, so that external flame can enter the lubricating oil cavity 101 through more than four corners no matter from the outer ring or the inner ring of the elastic shoulder, and the sealing assembly 30 positioned in the lubricating oil cavity 101 is almost impossible to burn, thereby playing a good role in protecting the sealing assembly 30, improving the lubricating oil sealing effect and reducing the test risk.
Optionally, as shown in fig. 1, the sealing assembly 30 includes a plurality of sealing rings 31 sequentially spaced apart along the axial direction of the elastic plug assembly 20. The outer circular surface of the elastic plug assembly 20 is correspondingly provided with a plurality of mounting ring grooves 201 for mounting a plurality of sealing rings 31 one by one, and the sealing rings 31 are mounted in the correspondingly arranged mounting ring grooves 201. In the fireproof structure, as shown in fig. 1, a sealing mode of a double O-shaped sealing ring is adopted, the O-shaped sealing ring is used for preventing lubricating oil from leaking, on one hand, the sealing effect of the double O-shaped sealing ring is better, on the other hand, the sealing structure has a better protection effect on fireproof, and even though a 1#O-shaped sealing ring close to a fireproof end is greatly deformed or melted under the high temperature condition, the 2#O-shaped sealing ring positioned at the rear of the sealing structure still has a good sealing effect and can prevent lubricating oil from leaking. In this alternative, as shown in fig. 2, the wall thickness c between two adjacent installation ring grooves 201 is greater than or equal to 1.5mm, so as to separate adjacent sealing rings, prevent mutual interference, and influence the sealing effect.
In this alternative, as shown in fig. 1, the connection between the inner side edge of the limiting ring groove 103 and the lubricating oil cavity 101 is chamfered circumferentially to form a guiding conical surface 104, and the design of the guiding conical surface 104 facilitates the smooth insertion of the elastic plug assembly 20 into the lubricating oil cavity 101. And in combination with the illustration in fig. 2, the axial distance b between the conical bottom of the guiding conical surface 104 and the nearest mounting ring groove 201 is more than or equal to 1.5mm, so that a certain distance between the sealing ring and the guiding conical surface is ensured, and the good sealing effect of the O-shaped sealing ring is ensured.
Alternatively, as shown in FIG. 1, the elastomeric closure assembly 20 includes a mounting closure 21 and a circlip 22. The installation blanking cover 21 includes blanking cover axis body 211 and spacing fender shoulder 212 that set gradually and link to each other along the axial, and after blanking cover axis body 211 was inserted oil slick chamber 101 by oil outlet channel 102, spacing fender shoulder 212 was spacing in spacing annular 103, and seal assembly 30 installs on the excircle of blanking cover axis body 211. The elastic retainer ring 22 is clamped in the limit ring groove 103 after being deformed, is positioned at the outer side of the mounting blanking cover 21, and is tightly attached to the mounting blanking cover 21 to form an elastic retainer shoulder. In this alternative, as shown in fig. 2, through the arrangement of the circlip 22, the circlip 22 can be clamped in the limiting ring groove 103, so that no matter the external flame passes through the outer ring or the inner ring of the circlip, the external flame can enter the lubricating oil cavity 101 through more than four corners, so that the two sealing rings 31 located in the lubricating oil cavity 101 are almost impossible to burn, thereby playing a good role in protecting the sealing assembly 30, improving the lubricating oil sealing effect, and in addition, the circlip 22 is additionally provided with a structural arrangement mode for installing the blocking cover 21, thereby being beneficial to the quick disassembly and assembly of the elastic blocking cover assembly 20.
In this alternative, as shown in fig. 1, the limiting ring groove 103 includes a first limiting groove and a second limiting groove that are sequentially disposed and communicated along the axial direction. The circlip 22 is clamped in the first limiting groove. The limiting stop shoulder 212 is located in the second limiting groove and abuts against the elastic retainer ring 22 after extending along the axial direction, so that two sides of the limiting stop shoulder 212 are respectively clung to the inner side face of the second limiting groove and the inner side face of the elastic retainer ring 22 under the action of the elastic retainer ring 22, and the outer side face of the elastic retainer ring 22 is clung to the outer side face of the first limiting groove.
In this alternative, as shown in fig. 2, the width f of the second limiting groove along the axial direction is greater than or equal to 2.5mm, so that the limiting shoulder 212 is ensured to have enough strength, and is not easy to deform in a fireproof test. The thickness e of the limiting stop shoulder 212 along the axial direction is more than or equal to f+0.1mm, so that the limiting stop shoulder 212 can be attached to the circlip 22. The radial height a of the limiting stop shoulder 212 is more than or equal to 3mm, so that the sufficient attaching area between the limiting stop shoulder 212 and the part 10 needing fire prevention is ensured, and a good flame isolation effect can be achieved. The radial distance d between the inner annular surface of the circlip 22 and the inner annular surface of the oil outlet passage 102 is more than or equal to 3mm, so that the circlip 22 is convenient to mount and dismount.
Preferably, as shown in fig. 1, the outer side surface of the first limiting groove is an inclined groove surface gradually inclined from the groove bottom to the outer side. The outer side surface of the circlip 22 is an inclined ring surface matched with the inclined groove surface of the first limit groove. In the preferred scheme, the arrangement mode of the elastic retainer ring 22 and the first limit groove can well compensate the clearance between the elastic retainer ring 22 and the limit ring groove 103 caused by machining tolerance on one hand; on the other hand, under the high temperature environment, each part will expand, and the limit stop shoulder 212 of the circlip 22 can automatically adapt to the change, so that as shown in fig. 2, two sides of the limit stop shoulder 212 are respectively clung to the inner side surface of the second limit groove and the inner side surface of the circlip 22, and the outer side surface of the circlip 22 is clung to the outer side surface of the first limit groove.
Optionally, as shown in fig. 1, an oil inlet channel 105 axially communicated with the oil cavity 101 is further provided in the part to be fireproof 10, and an oil inlet end of the oil inlet channel 105 is communicated with an oil tank. The aeroengine accessory case fireproof structure further comprises an elastic pressure relief assembly 40 which is elastically arranged in the oil sliding cavity 101, the outer side end of the elastic pressure relief assembly 40 is connected with an elastic blanking cover assembly 20, the opposite inner side end of the elastic pressure relief assembly is used for propping against an outlet of the oil inlet channel 105 when the oil pressure in the oil sliding tank is normal, and the elastic pressure relief assembly 40 is also used for axially shrinking after the oil pressure in the oil sliding tank exceeds the upper limit oil pressure so as to open the oil inlet channel 105 for pressure relief. When the oil pressure in the oil tank is normal, the inner side end of the elastic pressure relief assembly 40 is propped against the oil inlet channel 105, when the oil pressure in the oil tank exceeds the set upper limit oil pressure, the inner side end of the elastic pressure relief assembly 40 bears larger oil pressure, so that the whole oil pressure is contracted along the axial direction, the inner side end of the elastic pressure relief assembly 40 leaves the oil inlet channel 105, the oil in the oil tank is released into the oil chamber 101 and then is relieved, the oil tank is prevented from being burst due to overlarge pressure, and the accident is caused. Preferably, as shown in fig. 1, the part 10 to be fireproof is further provided with a pressure relief hole 106 communicated with the oil chamber 101, so that the oil leaked into the oil chamber 101 is leaked outwards through the pressure relief hole 106, and the problem of tightness between the elastic plug cover assembly 20 and the part 10 to be fireproof caused by excessive oil pressure in the oil chamber 101 is avoided.
In this alternative, as shown in fig. 1, the inner end of the blanking cover shaft body 211 of the installation blanking cover 21 is concavely extended to form a first installation cavity. The elastic pressure relief assembly 40 includes a mounting plug 41 and a spring 42 for providing an elastic force. The mounting plug 41 is concavely extended toward the outer end of the mounting plug cover 21 to form a second mounting cavity, the outer end of the mounting plug 41 is axially inserted into the first mounting cavity, and the opposite inner end is used for propping against the outlet of the oil inlet channel 105. The spring 42 is installed in the second installation cavity, and two axial ends respectively prop against the cavity bottom of the first installation cavity and the cavity bottom limit of the second installation cavity.
As shown in fig. 1, in order to prevent the oil tank from bursting due to excessive pressure in the oil tank during the test, thereby causing an accident due to the occurrence of a fire, in the present application, a mechanical pressure relief structure is adopted, and this function is accomplished by providing a mounting plug 41, a spring 42 and a pressure relief hole 106, when the oil tank pressure is excessive, the mounting plug 41 compresses the spring 42 to move left under the thrust force generated by the oil pressure to form a oil relief gap, and finally the pressure relief hole 106 is used to relieve the pressure, and the design of the mounting plug 41 needs to satisfy the following relation:
let P be the limit pressure of the lubricating oil tank, the compression amount of the spring 42 in the installation state is Deltax, the spring 42 stiffness of the spring 42 is k, the inner diameter of the oil inlet passage 105 is g, and the working safety coefficient is 0.8, the inner diameter g of the oil inlet passage 105 needs to satisfy the following relation:
the fire-proof structure of the aircraft engine accessory case has simple integral structure, adopts a mechanical pressure relief structure, works stably and reliably, greatly reduces the burst risk of the lubricating oil tank, and improves the test safety.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims (10)

1. An aircraft engine accessory receiver fire protection architecture, characterized in that includes:
the device comprises a part (10) to be fireproof, an elastic plug cover component (20) for sealing an end part and a sealing component (30) for sealing;
an oil sliding cavity (101) and an oil outlet channel (102) communicated with the oil sliding cavity (101) are arranged in the part (10) to be prevented from being corroded, and the inner wall surface of the oil outlet channel (102) is inwards concave to form a limit ring groove (103) close to the oil sliding cavity (101);
after the elastic plug cover assembly (20) is inserted into the oil sliding cavity (101) through the oil outlet channel (102), the elastic shoulder part at the outer end part of the elastic plug cover assembly is deformed and then clamped in the limit ring groove (103), so that external flame is prevented from entering the oil sliding cavity (101) through a gap between the elastic shoulder and the limit ring groove (103);
the sealing component (30) is arranged on the outer circle of the elastic blanking cover component (20) and is positioned between the elastic blanking cover component (20) and the lubricating oil cavity (101) so as to seal a gap between the elastic blanking cover component and the lubricating oil cavity.
2. The aircraft engine accessory case fire protection structure according to claim 1, wherein,
the sealing assembly (30) comprises a plurality of sealing rings (31) which are sequentially arranged at intervals along the axial direction of the elastic blanking cover assembly (20);
a plurality of mounting ring grooves (201) for mounting a plurality of sealing rings (31) one by one are correspondingly arranged on the outer circular surface of the elastic plug assembly (20), and the sealing rings (31) are mounted in the correspondingly arranged mounting ring grooves (201);
the wall thickness c between two adjacent mounting ring grooves (201) is more than or equal to 1.5mm.
3. The aircraft engine accessory case fire protection structure according to claim 2, wherein,
the connection part of the inner side edge of the limit ring groove (103) and the lubricating oil cavity (101) is chamfered circumferentially to form a guide conical surface (104);
the axial distance b between the conical bottom of the guide conical surface (104) and the nearest mounting ring groove (201) is more than or equal to 1.5mm.
4. The aircraft engine accessory case fire protection structure according to claim 2, wherein,
the elastic blanking cover assembly (20) comprises an installation blanking cover (21) and an elastic check ring (22);
the mounting blanking cover (21) comprises a blanking cover shaft body (211) and a limiting stop shoulder (212) which are sequentially arranged and connected along the axial direction, the limiting stop shoulder (212) is limited in the limiting ring groove (103) after the blanking cover shaft body (211) is inserted into the oil sliding cavity (101) from the oil outlet channel (102), and the sealing assembly (30) is arranged on the outer circle of the blanking cover shaft body (211);
the elastic retainer ring (22) is clamped in the limit ring groove (103) after being deformed, is positioned at the outer side of the installation blanking cover (21), and is tightly connected with the installation blanking cover (21) to form an elastic retainer shoulder.
5. The aircraft engine accessory case fire protection structure according to claim 4, wherein,
the limiting ring groove (103) comprises a first limiting groove and a second limiting groove which are sequentially arranged along the axial direction and communicated with each other;
the elastic retainer ring (22) is clamped in the first limit groove;
the limiting stop shoulder (212) is located in the second limiting groove and abuts against the elastic retainer ring (22) after extending along the axial direction, so that the two sides of the limiting stop shoulder (212) are respectively clung to the inner side face of the second limiting groove and the inner side face of the elastic retainer ring (22) under the action of the elastic retainer ring (22), and the outer side face of the elastic retainer ring (22) is clung to the outer side face of the first limiting groove.
6. The aircraft engine accessory case fire protection structure according to claim 5, wherein,
the width f of the second limit groove along the axial direction is more than or equal to 2.5mm;
the thickness e of the limiting stop shoulder (212) along the axial direction is more than or equal to f+0.1mm;
the height a of the limit stop shoulder (212) along the radial direction is more than or equal to 3mm;
the radial distance d between the inner annular surface of the elastic retainer ring (22) and the inner annular surface of the oil outlet channel (102) is more than or equal to 3mm.
7. The aircraft engine accessory case fire protection structure according to claim 5, wherein,
the outer side surface of the first limit groove is an inclined groove surface gradually inclined from the groove bottom to the outer side;
the outer side surface of the elastic retainer ring (22) is an inclined ring surface matched with the inclined groove surface of the first limit groove.
8. The aircraft engine accessory case fire protection structure according to claim 4, wherein,
an oil inlet channel (105) axially communicated with the oil slide cavity (101) is further arranged in the part (10) to be prevented from being corroded, and the oil inlet end of the oil inlet channel (105) is communicated with an oil slide tank;
the aeroengine accessory case fireproof structure further comprises an elastic pressure relief assembly (40) which is elastically arranged in the oil sliding cavity (101), the outer side end of the elastic pressure relief assembly (40) is connected with an elastic blanking cover assembly (20), the opposite inner side end of the elastic pressure relief assembly is used for propping against an outlet of the oil inlet channel (105) when the oil pressure in the oil sliding box is normal, and the elastic pressure relief assembly (40) is further used for axially shrinking after the oil pressure in the oil sliding box exceeds the upper limit oil pressure so as to open the oil inlet channel (105) for pressure relief.
9. The aircraft engine accessory case fire protection structure of claim 8, wherein,
the inner side end of a blanking cover shaft body (211) for installing the blanking cover (21) is concavely extended to form a first installation cavity;
the elastic pressure relief assembly (40) comprises a mounting plug (41) and a spring (42) for supplying elastic force;
the installation plug (41) is concavely extended towards the outer side end of the installation plug cover (21) to form a second installation cavity, the outer side end of the installation plug (41) is axially inserted into the first installation cavity, and the opposite inner side end of the installation plug is used for propping and blocking an outlet of the oil inlet channel (105);
the spring (42) is arranged in the second installation cavity, and the two axial ends respectively prop against the cavity bottom of the first installation cavity and the cavity bottom of the second installation cavity to limit.
10. The aircraft engine accessory case fire protection structure according to claim 9, wherein,
let P be the restriction pressure of the lubricating oil tank, the compression of the spring (42) in the installed state is Deltax, the rigidity of the spring (42) is k, the inner diameter of the oil inlet channel (105) is g, the working safety coefficient is 0.8, the inner diameter g of the oil inlet channel (105) needs to satisfy the following relation:
CN202310746638.9A 2023-06-25 2023-06-25 Fire-proof structure for accessory case of aeroengine Pending CN116928484A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310746638.9A CN116928484A (en) 2023-06-25 2023-06-25 Fire-proof structure for accessory case of aeroengine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310746638.9A CN116928484A (en) 2023-06-25 2023-06-25 Fire-proof structure for accessory case of aeroengine

Publications (1)

Publication Number Publication Date
CN116928484A true CN116928484A (en) 2023-10-24

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310746638.9A Pending CN116928484A (en) 2023-06-25 2023-06-25 Fire-proof structure for accessory case of aeroengine

Country Status (1)

Country Link
CN (1) CN116928484A (en)

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