CN116771920A - Aeroengine bearing cavity sealing device and aeroengine - Google Patents

Aeroengine bearing cavity sealing device and aeroengine Download PDF

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Publication number
CN116771920A
CN116771920A CN202210232507.4A CN202210232507A CN116771920A CN 116771920 A CN116771920 A CN 116771920A CN 202210232507 A CN202210232507 A CN 202210232507A CN 116771920 A CN116771920 A CN 116771920A
Authority
CN
China
Prior art keywords
ring
sealing
annular
aeroengine
cavity
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
CN202210232507.4A
Other languages
Chinese (zh)
Inventor
王计辉
俞镪鹏
李铠月
韩宁
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.)
AECC Commercial Aircraft Engine Co Ltd
Original Assignee
AECC Commercial Aircraft Engine Co Ltd
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 AECC Commercial Aircraft Engine Co Ltd filed Critical AECC Commercial Aircraft Engine Co Ltd
Priority to CN202210232507.4A priority Critical patent/CN116771920A/en
Publication of CN116771920A publication Critical patent/CN116771920A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • F16J15/3248—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings provided with casings or supports
    • 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
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/26—Sealings between relatively-moving surfaces with stuffing-boxes for rigid sealing rings
    • F16J15/30—Sealings between relatively-moving surfaces with stuffing-boxes for rigid sealing rings with sealing rings made of carbon
    • 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
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
    • F16J15/3268—Mounting of sealing rings
    • 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
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
    • F16J15/3436—Pressing means
    • F16J15/344—Pressing means the pressing force being applied by means of an elastic ring supporting the slip-ring
    • 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
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/16—Sealings between relatively-moving surfaces
    • F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
    • F16J15/3464—Mounting of the seal

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

Abstract

The application relates to an aeroengine bearing cavity sealing device and an aeroengine, wherein the aeroengine bearing cavity sealing device comprises: an annular member configured to be capable of being fitted over a rotor of an aircraft engine; the sealing seat is sleeved outside the annular component and is used for being sleeved in a casing of the aeroengine, an annular cavity is arranged on the inner surface of the sealing seat, and at least one end of the annular cavity along the axial direction of the annular component is a closed end; a push ring sleeved between the annular component and the sealing seat and positioned in the annular cavity, wherein the push ring is configured to swing in a plane passing through the axis of the annular component; the graphite seal ring is sleeved between the annular component and the seal seat and is arranged in the annular cavity along the axial direction of the annular component side by side with the push ring, and comprises a first sealing surface in contact with the annular component and a second sealing surface in contact with the push ring; the elastic sealing ring is arranged on one side of the push ring, which is far away from the graphite sealing ring, one side of the elastic sealing ring is in sealing fit with the sealing seat of the closed end of the annular cavity, and the other side of the sealing ring is in sealing fit with the push ring.

Description

Aeroengine bearing cavity sealing device and aeroengine
Technical Field
The application relates to the technical field of aviation, in particular to an aero-engine bearing cavity sealing device and an aero-engine.
Background
Aeroengines typically use rolling bearings to create a rotor support system, which requires constant lubrication and cooling of the bearings with lubricating oil in order to ensure high performance and long life operation of the bearings. The main bearing cavity of the aeroengine is sealed, and the main bearing cavity is isolated from the air path environment, so that lubricating oil in the bearing cavity is effectively prevented from being interfered by the air path environment, and the lubricating oil in the bearing cavity is prevented from leaking. As performance metrics of modern aeroengines evolve towards low noise, low fuel consumption, low emissions, gear driven fan (GTF) configurations are being proposed to be very beneficial for noise reduction, emissions reduction and fuel economy improvement, but the gear train of GTF configured aeroengines is subject to inertial forces and gyroscopic moments, resulting in angular runout of the engine rotor (related research data is no greater than 0.5 °). The main bearing cavity seal of GTF configuration aeroengines needs to be able to accommodate angular runout and eccentricity of the rotor. The circumferential graphite seal is widely used for sealing main bearing cavities of active aeroengines, and has a plurality of incomparable advantages compared with other types of seals, such as stronger sealing performance under the condition of the same volume; the rotor axial displacement is more contained; the seal maintains device integrity in the event of accidental damage in harsh environments. However, the leakage rate of the circumferential graphite seal is remarkably increased when the rotor deflects, and the sealing performance is seriously affected. Related researches show that when the deflection angle of the circumferential graphite seal is 0 degree, the leakage rate of the seal gas is in the order of 1E-5kg/s, and when the deflection angle is 0.1 degree, the leakage rate of the seal gas is in the order of 1E-2kg/s, and the leakage rate of the seal gas is in a linear increasing trend along with the increase of the deflection angle. Meanwhile, the graphite sealing ring works for a long time in a deflection state, so that the sealing life of the circumferential graphite is shortened drastically, and failures of different degrees occur.
Disclosure of Invention
The application aims to provide an aeroengine bearing cavity sealing device and an aeroengine, so as to solve the problem that a circumferential graphite sealing component is easy to leak when a rotor of the aeroengine deviates from an axis of the aeroengine in the prior art.
According to one aspect of an embodiment of the present application, there is provided an aero-engine bearing cavity seal arrangement, comprising:
an annular member configured to be capable of being fitted over a rotor of an aircraft engine;
the sealing seat is sleeved outside the annular component and is used for being sleeved in a casing of the aeroengine, an annular cavity is arranged on the inner surface of the sealing seat, and at least one end of the annular cavity along the axial direction of the annular component is a closed end;
a push ring sleeved between the annular component and the sealing seat and positioned in the annular cavity, wherein the push ring is configured to swing in a plane passing through the axis of the annular component;
the graphite seal ring is sleeved between the annular component and the seal seat and is arranged in the annular cavity along the axial direction of the annular component side by side with the push ring, and comprises a first sealing surface in contact with the annular component and a second sealing surface in contact with the push ring;
the elastic sealing ring is arranged on one side of the push ring, which is far away from the graphite sealing ring, one side of the elastic sealing ring is in sealing fit with the sealing seat of the closed end of the annular cavity, and the other side of the sealing ring is in sealing fit with the push ring.
In some embodiments, in a cross section of the elastic sealing ring, a side of the elastic sealing ring facing the closed end of the annular cavity is an arc-shaped structure protruding towards the closed end, and a side of the elastic sealing ring facing the push ring is an arc-shaped structure protruding towards the push ring.
In some embodiments, the elastomeric seal ring comprises:
a jacket having a ring shape and a cavity in its cross section;
an energy storage spring is disposed in the cavity and configured to urge the collet toward the push ring and the closed end.
In some embodiments, the energy storage spring is an annular structure sleeved in the jacket, and the cross section of the energy storage spring is one of an O-shaped structure, a U-shaped structure and a V-shaped structure.
In some embodiments, the aero-engine bearing cavity sealing device further comprises a first resilient member configured to urge the graphite seal ring toward the push ring.
In some embodiments, the aeroengine bearing cavity sealing device further comprises an elastic component mounting seat mounted at one end of the annular cavity far away from the closed end, one end of the first elastic component is abutted with the graphite sealing ring, and the other end of the first elastic component is abutted with the elastic component mounting seat.
In some embodiments, the device further comprises a second elastic member configured to push the push ring toward the closed end of the annular cavity, one end of the second elastic member being in abutment with the push ring, the other end of the second elastic member being in abutment with the elastic member mount.
In some embodiments, the elastomeric mount and seal mount are in a non-rotational fit.
In some embodiments, the graphite seal ring comprises a plurality of graphite arc segments arranged in sequence and separately along the circumference of the annular component, and the aeroengine bearing cavity sealing device further comprises an elastic bundling component sleeved outside the plurality of graphite arc segments to mount the plurality of graphite arc segments on the annular component.
In some embodiments, the resilient strapping member includes a spring extending in a circumferential direction of the graphite seal ring.
In some embodiments, the push ring is in a non-rotational engagement with the seal seat.
In some embodiments, the aeroengine bearing cavity sealing device further comprises a helical structure for pushing lubricating oil towards the bearing cavity of the seal holder during rotation of the annular member with the rotor of the aeroengine.
In some embodiments, the helical structure includes a helical groove provided on an inner circumferential surface of the seal seat, the helical groove being provided on a side of the annular cavity adjacent the bearing cavity.
In some embodiments of the present application, in some embodiments,
the outer peripheral surface of the graphite sealing ring is provided with a first unloading groove extending along the axial direction of the graphite sealing ring and a fluid channel communicated with the first unloading groove and a pressurizing cavity of the aero-engine; and
and a second unloading groove communicated with the pressurizing cavity of the aeroengine is arranged on the end surface of the graphite sealing ring adjacent to the push ring.
In some embodiments, the aero-engine bearing cavity sealing device further comprises a cooling system for cooling the graphite seal ring and the annular member 12, the cooling system comprising an annular groove provided in the annular member for containing a cooling medium, the annular groove extending in an axial direction of the annular member and having an open end at an end of the annular member adjacent the bearing cavity.
According to another aspect of the application, there is also provided an aeroengine comprising an aeroengine bearing cavity sealing device as described above.
By applying the technical scheme of the application, the push ring is configured to swing in a plane passing through the axis of the annular component, namely, the included angle between the push ring and the axis direction of the annular component is adjustable, and under the condition that the annular component deviates from the axis direction of the aeroengine along with the rotor of the aeroengine, the push ring adjusts the included angle between the push ring and the axis direction of the annular component under the pushing of the graphite seal ring sleeved on the annular component, so that the second sealing surface of the graphite seal ring is fully contacted with the push ring, and the sealing effect between the graphite seal ring and the push ring is ensured.
Other features of the present application and its advantages will become apparent from the following detailed description of exemplary embodiments of the application, which proceeds with reference to the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the application or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the application, and that other drawings can be obtained according to these drawings without inventive faculty for a person skilled in the art.
FIG. 1 shows a schematic structural view of an aero-engine bearing cavity seal arrangement according to an embodiment of the present application;
FIG. 2 shows a partial enlarged view of FIG. 1;
FIG. 3 shows a schematic cross-sectional view of an aero-engine bearing cavity seal arrangement at another angle in the circumferential direction of an embodiment of the present application; and
FIG. 4 shows a schematic view of the structure of an elastic sealing ring of one of the sealing devices of the bearing cavity of an aero-engine according to an embodiment of the present application;
FIG. 5 shows a schematic view of another elastomeric seal ring configuration of an aero-engine bearing cavity seal arrangement in accordance with an embodiment of the present application;
FIG. 6 shows a schematic view of another elastomeric seal ring configuration of an aero-engine bearing cavity seal arrangement in accordance with an embodiment of the present application;
FIG. 7 shows a schematic view of the location of the sealing points of an aero-engine bearing cavity sealing device of an embodiment of the present application;
FIG. 8 shows a schematic structural view of a seal seat of an aero-engine bearing cavity seal arrangement according to an embodiment of the present application;
FIG. 9 shows a schematic structural view of a push ring of an aero-engine bearing cavity seal arrangement according to an embodiment of the present application; and
fig. 10 shows a schematic structural view of an elastomeric mount of an aero-engine bearing cavity seal device according to an embodiment of the present application.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
As shown in connection with fig. 1 to 3, a bearing chamber sealing device comprising a circumferential graphite sealing ring is arranged between a bearing chamber a of a bearing of an aircraft engine, in which a main shaft is arranged, and a pressurizing chamber B. The bearing cavity A is filled with an oil-gas mixture, the pressurizing cavity B is filled with air, and under normal working conditions, the air pressure of the pressurizing cavity B is higher than that of the bearing cavity A, and the bearing cavity sealing device can effectively seal lubricating oil in the bearing cavity A and limit excessive air in the pressurizing cavity B from flowing into the bearing cavity.
The aeroengine bearing cavity sealing device of the embodiment comprises an annular component 12, the annular component 12, a sealing seat 2, a push ring 3, a graphite sealing ring 7 and an elastic sealing ring 5.
The annular member 12 is configured to fit over the rotor of an aircraft engine. The sealing seat 2 is sleeved outside the annular component 12 and is used for being sleeved in a casing of the aeroengine, an annular cavity is arranged on the inner surface of the sealing seat 2, and at least one end of the annular cavity along the axial direction of the annular component 12 is a closed end 205. The push ring 3 is sleeved between the annular member 12 and the seal seat 2 and is located in the annular cavity, the push ring 3 being configured to be swingable in a plane passing through the axis of the annular member 12.
The graphite seal ring 7 is disposed between the annular member 12 and the seal holder 2 and is disposed in the annular cavity side by side with the push ring 3 in the axial direction of the annular member 12, and the graphite seal ring 7 includes a first seal surface 701 in contact with the annular member 12 and a second seal surface 702 in contact with the push ring 3.
The elastic sealing ring 5 is arranged on one side of the push ring 3 far away from the graphite sealing ring 7, one side of the elastic sealing ring 5 is in sealing fit with the sealing seat 2 of the closed end 205 of the annular cavity, and the other side of the sealing ring 5 is in sealing fit with the push ring 3.
In the technical solution of this embodiment, the push ring 3 is configured to swing in a plane passing through the axis of the annular component 12, that is, the included angle between the push ring 3 and the axis direction of the annular component 12 is adjustable, and when the annular component 12 deviates from the axis direction of the aeroengine along with the rotor of the aeroengine, the push ring 3 adjusts the included angle between the push ring 3 and the axis direction of the annular component 12 under the pushing of the graphite seal ring 7 sleeved on the annular component 12, so as to ensure that the second sealing surface 702 of the graphite seal ring 7 is fully contacted with the push ring 3, thereby ensuring the sealing effect between the graphite seal ring 7 and the push ring 3. Further, the graphite seal ring 7 is fixedly sleeved on the annular member 12, so that the first sealing surface 701 of the graphite seal ring 7 can be kept in sufficient contact with the peripheral surface of the annular member 12 to ensure the sealing effect between the graphite seal ring 7 and the annular member 12.
In some embodiments, the outer circumference of the push ring 3 is in clearance fit with the mount 2 and/or the inner circumference of the push ring 3 is in clearance arrangement with the annular member 12 to allow the push ring 3 to swing flexibly under the bias of the graphite seal ring 7.
The elastic sealing ring 5 is used for sealing between the push ring 3 and the mounting seat 2 of the closed end 205 of the annular cavity, and the elastic sealing ring 5 and the graphite sealing ring 7 are matched to seal the bearing cavity.
In the cross section of the elastic sealing ring 5, the side of the elastic sealing ring 5 facing the closed end 205 of the annular cavity is of an arc-shaped structure protruding towards the closed end 205, and the side of the elastic sealing ring 5 facing the push ring 3 is of an arc-shaped structure protruding towards the push ring 3, so that when the push ring 3 deviates from a position perpendicular to the axis of the annular component 12 under the pushing of the graphite seal ring 7, a good seal is formed between the elastic sealing ring 5 and the push ring 3 and the mounting seat 2.
As shown in fig. 4 to 6, in some embodiments, the elastic sealing ring 5 comprises a jacket 501 and an energy storage spring 502, the jacket 501 being annular and having a cavity in its cross section; an energy storage spring 502 is disposed in the cavity and is configured to urge the collet 501 toward the push ring 3 and the closed end 205.
The energy storage spring 502 is an annular structure sleeved in the jacket 501, and the cross section of the energy storage spring 502 is one of an O-shaped structure (shown in fig. 4), a U-shaped structure (shown in fig. 5) and a V-shaped structure (shown in fig. 6).
The elastic sealing ring 5 is pressed on the sealing seat 2 of the closed end 205 of the annular cavity by the acting force transmitted to the push ring 3 by the second elastic component 4. On the one hand, the elastic sealing ring 5 forms a good static seal 505 with self-tightening capability between the push ring 3 and the sealing seat 2, and the sealing point is shown in fig. 7; on the other hand, when there is angular deflection of the annular member 12 (the axis of the annular member 12 is offset from the axis of the engine), the amount of deflection imparted to the push ring 3 by the graphite seal ring 7 is compensated for by the elastomeric seal ring 5. Related researches show that the elastic sealing ring 5 does not influence the static sealing performance under the condition of small-angle deflection. It should be noted that, in order to meet the requirement that the push ring 3 can smoothly deflect along with the graphite seal ring 7 in the angular direction, the fit clearance between the push ring 3 and the seal seat 2 needs to be designed reasonably, and the clearance value should be greater than the product of the tangent value of the maximum deflection angle multiplied by the axial thickness value of the push ring 3.
As shown in fig. 1 to 3, the aero-engine bearing cavity sealing device further comprises a first elastic member 6 configured to urge the graphite seal ring 7 towards the push ring 3.
The aeroengine bearing cavity sealing device further comprises an elastic component mounting seat 9 arranged at one end, far away from the closed end 205, of the annular cavity, one end of the first elastic component 6 is abutted with the graphite sealing ring 7, and the other end of the first elastic component is abutted with the elastic component mounting seat 9.
The aeroengine bearing cavity sealing device further comprises a second elastic member 4 configured to push the push ring 3 towards the closed end 205 of the annular cavity, one end of the second elastic member 4 is abutted against the push ring 3, and the other end of the second elastic member 4 is abutted against the elastic member mounting seat 9.
The graphite seal ring 7 comprises a plurality of graphite arc segments which are sequentially arranged along the circumference of the annular component 12 and are arranged in a split mode, the aeroengine bearing cavity sealing device further comprises an elastic bundling component 8, and the elastic bundling component 8 is sleeved outside the graphite arc segments so as to install the graphite arc segments on the annular component 12.
In some embodiments, the strapping member 8 comprises an annular spring extending in the circumferential direction of the graphite seal ring 7.
Specifically, the graphite sealing ring 7 comprises at least three graphite arc sections with the same characteristics, and joint planes of two adjacent graphite arc sections are tightly abutted with each other. The outer circumferential surface of the graphite arc segments is provided with a circumferential groove 704, and the strapping unit 8 is mounted in the circumferential groove, and the strapping unit 8 uniformly clamps the lapped graphite arc segments on the annular unit 12 to form a circumferential seal with an initial radial contact load. The contact surface of the seal ring-shaped part 12 and the graphite seal ring 7 is a first sealing surface 701; at least two first elastic member mounting holes 705 are provided on the first end face side of the graphite arc-shaped segment. The first resilient member mounting hole 705 is a blind hole. The first elastic member 6 can be inserted into the first elastic member mounting hole 705, so that each graphite arc segment is pressed against the side end surface of the push ring 3, an initial axial contact load is provided, and the contact surface between the side end surface of the push ring 3 and the graphite seal ring is the second sealing surface 702.
The inner circumference of the graphite seal ring 7 is provided with at least one annular first unloading groove 707 and at least one fluid channel 706 which extends along the axial direction of the graphite seal ring 7 and is communicated with the first unloading groove 707, the fluid channel 706 separates the inner circumference surface of the graphite seal ring 7 into a concave part and a convex part with annular intervals, and gas is uniformly distributed in the unloading groove 707 and the fluid channel 706 so as to balance the radial load of a part of the graphite seal ring. The end face of the graphite seal ring 7 near one end of the push ring 3 is provided with a second unloading groove 703 communicated with the pressurizing cavity B for balancing the axial load of a part of the graphite seal ring 7.
At least three second elastic member mounting holes 301 are provided on the first end face 302 side of the push ring 3. The second elastic member mounting hole is a blind hole, and the second elastic member 4 can be inserted into the second elastic member mounting hole 301. In some embodiments, the number of second resilient member mounting holes on the side of the first end face 302 is 12. As shown in fig. 2; the second end surface 303 side of the push ring is provided with a ring groove 304, and the elastic sealing ring 5 can be installed in the ring groove 304. The elastic sealing ring 5 is a spring energy storage sealing ring.
As shown in fig. 1 to 3 and 10, the elastic member mount 9 is provided with a first annular groove surface 901 which contacts the second elastic member 4 and a second annular groove surface 902 which contacts the first elastic member 6, respectively. The elastic member mounting seat 9 is provided with an anti-rotation pin 903, and one end of the graphite sealing ring 7, which is close to the elastic member mounting seat 9, is provided with an anti-rotation pin groove 708. The space positions and the number of the anti-rotation pins 903 are in one-to-one correspondence with the anti-rotation pin grooves 708 of the graphite seal ring 7.
In some embodiments, as shown in fig. 10, the number of anti-rotation pins is 3, and the second annular groove surface 902 keeps away from the position of the anti-rotation pins. As shown in fig. 3, the rotation preventing pin 903 is fitted into the rotation preventing pin groove 708 to restrict the rotation of the graphite seal ring 7 with the annular member 12, but does not restrict the degree of freedom of the graphite seal ring 7 in the radial direction of the annular member 12, so that the graphite seal ring 7 has followability to the radial runout of the annular member 12. The other side surface of the elastic component mounting seat 9 is in contact with the baffle 10 and is axially fixed.
The baffle 10 is fitted into the groove 202 of the seal holder 2, and the outer circumferential surface of the baffle 10 is in clearance with the inner circumferential surface of the groove 202 of the seal holder 2, and the end face thereof is axially fixed by the collar 11. The collar 11 is fitted into the clamping groove 203 of the seal holder 2, and the outer circumferential surface of the collar 2 is tightly fitted to the clamping groove 203 of the seal holder 2, so that the collar 2 is not allowed to move axially in the clamping groove 203.
In some embodiments, the push ring 3 is in anti-rotation fit with the mounting seat 2, and the aeroengine bearing cavity sealing device further comprises a first anti-rotation structure for limiting rotation of the push ring 3 relative to the mounting seat 2, wherein the first anti-rotation structure comprises an anti-rotation boss 204 (shown in fig. 8) and a first anti-rotation groove 305 (shown in fig. 9) matched with the anti-rotation boss, and one anti-rotation boss 204 and the first anti-rotation groove 305 are arranged on the outer peripheral surface of the push ring 3, and the other anti-rotation boss and the first anti-rotation groove 305 are arranged on the inner peripheral surface of the mounting seat 2.
In some embodiments, the elastic member mounting seat 9 is in anti-rotation fit with the mounting seat 2, the aeroengine bearing cavity sealing device further comprises a second anti-rotation structure for limiting rotation of the elastic member mounting seat 9 relative to the mounting seat 2, the second anti-rotation structure comprises an anti-rotation boss 204 (as shown in fig. 8) and a second anti-rotation groove 904 (as shown in fig. 10) matched with the anti-rotation boss 204, wherein one of the anti-rotation boss 204 and the second anti-rotation groove 904 is arranged on the outer peripheral surface of the elastic member mounting seat 9, and the other is arranged on the inner peripheral surface of the mounting seat 2.
The aeroengine bearing cavity sealing device is characterized by further comprising a cooling system 1 for cooling the graphite seal ring 7 and the annular component 12, wherein the cooling system 1 comprises an annular groove 1201 which is arranged on the annular component 12 and is used for containing cooling medium, and the annular groove 1201 extends along the axial direction of the annular component 12 and is provided with an open end at one end of the annular component 12 adjacent to the bearing cavity A.
The aeroengine bearing cavity sealing device further comprises a helical structure for pushing lubricating oil towards the bearing cavity a of the seal housing 2 during rotation of the annular member 12 with the rotor of the aeroengine.
The spiral structure includes a spiral groove 201 provided on the inner peripheral surface of the seal holder 2, the spiral groove 201 being provided on a side of the annular cavity adjacent to the bearing cavity a.
In the working state, the sealing runway rotates along with the aero-engine rotor at a high speed, the graphite seal ring 7 at the first sealing surface 701 of the circumferential graphite seal and the sealing runway 12 rub mutually to generate friction heat, and the graphite seal ring 7 at the second sealing surface 702 is affected by factors such as runout of the sealing runway 12 and the like to mutually perform micro-friction with the side surface of the push ring 3 to generate friction heat. The friction heat of the circumferential graphite seal is cooled by spraying cooling lubricating oil, so that the lubricating oil cannot directly wash the heat generating surface of the circumferential graphite seal, and heat exchange is performed by adopting a partition wall cooling mode in order to protect the working environment of the graphite seal ring and reduce lubricating oil leakage. The oil supply conduit 101 of the cooling system 1 is filled with the lubricating oil for cooling, the lubricating oil is injected into the annular groove 1201 of the sealing runway 12 by the oil supply nozzle 102 at the flow speed of 10-12m/s, the lubricating oil and the sealing runway perform convection heat exchange, the friction heat transferred to the sealing runway in a heat conduction mode is fully transferred out, and the lubricating oil is finally thrown into the bearing cavity A by the sealing runway 12 rotating at a high speed.
Oil and gas swirling in the bearing chamber a or oil injection of the cooling system 1 and high speed revolution of the sealing race 12 may cause oil contamination of the circumferential graphite seal. The radial inner circumferential surface of the sealing seat 2 is provided with a reverse spiral groove 201 along the axial direction, the reverse spiral groove 201 has the function of reversely conveying the lubricating oil in the rotating process of the sealing runway 12, and the lubricating oil can be prevented from entering the vicinity of the first sealing surface 701 and the second sealing surface 702 of the circumferential graphite seal, so that the sustainable operation of the circumferential graphite seal is effectively protected.
In the working state, when the rotor of the engine swings at a certain angle, the sealing runway 12 fixed with the rotor swings at the same angle. The graphite seal ring 7, which is attached to the annular part 12, is deflected with the annular part. The graphite seal ring 7 is axially acted by the spring force of the first elastic component 6 and is always pressed on the side surface of the push ring 3, so that the push ring 3 is in adaptive angular deflection, finally the angular deflection of the graphite seal ring 7 is elastically compensated by the spring energy storage sealing ring 5 arranged on the push ring 3, and the deflection angle of the graphite seal ring 7, the push ring 3 and the annular component 12 is relatively 0 degrees, namely, the first sealing surface 701 and the second sealing surface 702 always keep the best working state.
In the working state, when the rotor of the engine jumps, the annular part 12 fixed with the rotor jumps in the same scale. In order to ensure good sealing properties of the first sealing surface 701, the graphite sealing ring 7 of the anchor ring on the annular part 12 needs to be able to follow the runout of the annular part 12, i.e. the spring force of the first elastic part 6 needs to be matched to the spring force of the elastic strapping part 8. When the ring-shaped component 12 is subjected to jumping phenomenon, the graphite sealing ring 12 can overcome the friction force of the second sealing surface 702, and the suspension effect is avoided. The relative friction force of the graphite seal ring 7 and the push ring 3 causes the push ring 3 to have a relative movement tendency, and finally the friction force is transmitted to the spring energy storage sealing ring 5 arranged on the push ring 3. Related researches show that under the condition of meeting the working compression, the friction force between the spring energy storage sealing ring 5 and the adjacent part is more than 500N, and is far more than the sliding friction force between the graphite sealing ring 12 and the push ring 3. Namely, when the rotor jumps, the spring energy storage sealing ring 5 always meets the working requirement of static seal, and the auxiliary seal formed by the spring energy storage sealing ring 5 and the push ring 3 can always maintain a static state, so that the normal work of circumferential graphite seal is not influenced.
Compared with the traditional circumferential graphite seal, the circumferential graphite seal device with the auxiliary seal can improve the seal effect when the rotor of the aeroengine deflects, and effectively reduce the leakage rate and abrasion of the circumferential graphite seal caused by the deflection of the rotor.
The foregoing is illustrative of the present application and is not to be construed as limiting thereof, but rather, any modification, equivalent replacement, improvement or the like which comes within the spirit and principles of the present application are intended to be included within the scope of the present application.

Claims (16)

1. An aeroengine bearing cavity sealing device, comprising:
an annular member (12) configured to be able to fit over a rotor of an aircraft engine;
the sealing seat (2) is sleeved outside the annular component (12) and is used for being sleeved in a casing of the aeroengine, an annular cavity is arranged on the inner surface of the sealing seat (2), and at least one end of the annular cavity along the axial direction of the annular component (12) is a closed end (205);
a push ring (3) sleeved between the annular member (12) and the seal seat (2) and located in the annular cavity, the push ring (3) being configured to be swingable in a plane passing through the axis of the annular member (12);
a graphite seal ring (7) which is sleeved between the annular component (12) and the seal seat (2) and is arranged in the annular cavity side by side with the push ring (3) along the axial direction of the annular component (12), wherein the graphite seal ring (7) comprises a first seal surface (701) contacted with the annular component (12) and a second seal surface (702) contacted with the push ring (3);
the elastic sealing ring (5) is arranged on one side, far away from the graphite sealing ring (7), of the push ring (3), one side of the elastic sealing ring (5) is in sealing fit with the sealing seat (2) of the closed end (205) of the annular cavity, and the other side of the sealing ring (5) is in sealing fit with the push ring (3).
2. Aeroengine bearing cavity sealing device according to claim 1, wherein in the cross section of the elastic sealing ring (5), the side of the elastic sealing ring (5) facing the closed end (205) of the annular cavity is an arc-shaped structure protruding towards the closed end (205), and the side of the elastic sealing ring (5) facing the push ring (3) is an arc-shaped structure protruding towards the push ring (3).
3. Aeroengine bearing cavity sealing device according to claim 2, wherein said elastic sealing ring (5) comprises:
a jacket (501) having a ring shape and a cavity in its cross section;
an energy storage spring (502) is disposed in the cavity and configured to urge the collet (501) toward the push ring (3) and the closed end (205).
4. The aeroengine bearing cavity sealing device according to claim 3, wherein the energy storage spring (502) is of an annular structure sleeved in the jacket (501), and the cross section of the energy storage spring (502) is one of an O-shaped structure, a U-shaped structure and a V-shaped structure.
5. Aeroengine bearing cavity sealing device according to claim 1, further comprising a first elastic member (6) configured to urge the graphite seal ring (7) towards the push ring (3).
6. The aeroengine bearing cavity sealing device according to claim 5, further comprising an elastic member mounting seat (9) mounted at an end of the annular cavity remote from the closed end (205), one end of the first elastic member (6) being in abutment with the graphite sealing ring (7) and the other end being in abutment with the elastic member mounting seat (9).
7. The aeroengine bearing cavity sealing device according to claim 6, further comprising a second elastic member (4) configured to push the push ring (3) towards the closed end (205) of the annular cavity, one end of the second elastic member (4) being in abutment with the push ring (3), the other end of the second elastic member (4) being in abutment with the elastic member mount (9).
8. Aeroengine bearing cavity sealing device according to claim 6, wherein the resilient member mounting seat (9) and the sealing seat (2) are in a non-rotational fit.
9. The aeroengine bearing cavity sealing device according to claim 1, wherein the graphite seal ring (7) comprises a plurality of graphite arc segments which are sequentially arranged along the circumferential direction of the annular component (12) and are separately arranged, the aeroengine bearing cavity sealing device further comprises an elastic bundling component (8), and the elastic bundling component (8) is sleeved outside the plurality of graphite arc segments so as to install the plurality of graphite arc segments on the annular component (12).
10. Aeroengine bearing cavity sealing device according to claim 8, wherein said elastic strapping means (8) comprise springs extending in the circumferential direction of said graphite sealing ring (7).
11. Aeroengine bearing cavity sealing device according to claim 1, wherein the push ring (3) is in a non-rotational fit with the sealing seat (2).
12. Aeroengine bearing cavity sealing device according to claim 1, further comprising a screw structure for pushing lubricating oil towards the bearing cavity (a) of the sealing seat (2) during rotation of the annular member (12) with the rotor of the aeroengine.
13. Aeroengine bearing cavity sealing device according to claim 12, wherein the spiral structure comprises said spiral groove (201) provided on the inner peripheral surface of the sealing seat (2), said spiral groove (201) being provided on a side of the annular cavity adjacent to the bearing cavity (a).
14. The aeroengine bearing cavity sealing device of claim 1, wherein the sealing device comprises a sealing device,
a first unloading groove (707) extending along the axial direction of the graphite sealing ring (7) and a fluid channel (706) communicating the first unloading groove (707) with a pressurizing cavity (B) of the aeroengine are arranged on the peripheral surface of the graphite sealing ring; and
and a second unloading groove (703) communicated with a pressurizing cavity (B) of the aeroengine is formed in the end face, adjacent to the push ring (3), of the graphite sealing ring (7).
15. Aeroengine bearing cavity sealing device according to claim 1, further comprising a cooling system (1) for cooling down said graphite seal ring (7) and said annular member 12, the cooling system (1) comprising an annular groove (1201) provided in the annular member (12) for receiving a cooling medium, the annular groove (1201) extending in the axial direction of the annular member (12) and having an open end at an end of the annular member (12) adjacent to the bearing cavity (a).
16. An aircraft engine comprising an aircraft engine bearing cavity sealing device according to any one of claims 1 to 15.
CN202210232507.4A 2022-03-09 2022-03-09 Aeroengine bearing cavity sealing device and aeroengine Pending CN116771920A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210232507.4A CN116771920A (en) 2022-03-09 2022-03-09 Aeroengine bearing cavity sealing device and aeroengine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210232507.4A CN116771920A (en) 2022-03-09 2022-03-09 Aeroengine bearing cavity sealing device and aeroengine

Publications (1)

Publication Number Publication Date
CN116771920A true CN116771920A (en) 2023-09-19

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210232507.4A Pending CN116771920A (en) 2022-03-09 2022-03-09 Aeroengine bearing cavity sealing device and aeroengine

Country Status (1)

Country Link
CN (1) CN116771920A (en)

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