A graphite seal structure for sealing an inter-rotor oil cavity of an aero-engine

Abstract

A graphite sealing structure for sealing an aero-engine inter-rotor oil chamber, comprising a high-pressure turbine rotor and a low-pressure turbine rotor, an outer cover sleeved on the high-pressure turbine rotor, a stop ring and a rear thrust ring both sleeved on the outer cover, a front end surface of the stop ring being tightly combined with the high-pressure turbine rotor, rubber sealing rings being arranged between the stop ring, the rear thrust ring and the outer cover, a plurality of graphite ring assemblies being sleeved on the outer cover, and intermediate rings being arranged between adjacent graphite ring assemblies, each graphite ring assembly comprising a front sealing ring, a rear sealing ring and an elastic member for forming an axial thrust on the front and rear sealing rings, a front end surface of the front sealing ring of each graphite ring assembly being in sealing cooperation with a rear end surface of the stop ring or an intermediate ring, a rear end surface of the rear sealing ring being in sealing cooperation with a front end surface of the intermediate ring or the rear thrust ring, an outer peripheral surface of the front and rear sealing rings being in sealing cooperation with an inner peripheral surface of the low-pressure turbine rotor, and openings being respectively arranged on the front and rear sealing rings to form an open ring structure.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, and particularly relates to a graphite sealing structure for sealing a lubricating oil cavity between rotors of an aero-engine. BACKGROUND

[0002] In an aero-engine, aviation lubricating oil is generally used to lubricate and dissipate heat of main fulcrum bearings of the engine, and a graphite sealing device is mainly used to seal a lubricating oil cavity in a turbofan engine, and the structure of the graphite sealing device is divided into a rotor-to-rotor sealing structure and a rotor-to-stator sealing structure according to application positions, and the two structures are quite different.

[0003] During operation of the engine, high and low pressure turbine rotors rotate at high speed, and the sealing position is in a complex working condition environment, and how to make the graphite sealing assembly work stably under the conditions of a certain rotating speed, temperature, vibration and pressure difference can ensure that the lubricating oil does not leak or only a small amount of leakage is allowed, and effective sealing between the air cavity and the lubricating oil cavity is achieved. SUMMARY

[0004] The main purpose of the present application is to provide a graphite sealing structure for sealing a lubricating oil cavity between rotors of an aero-engine, which aims to solve the above technical problems.

[0005] To achieve the above purpose, the present application provides a graphite sealing structure for sealing a lubricating oil cavity between rotors of an aero-engine, which comprises a high pressure turbine rotor and a low pressure turbine rotor, and further comprises:

[0006] an outer cover sleeved on the high pressure turbine rotor;

[0007] a stop ring and a rear thrust ring, which are sleeved on the outer cover and are spaced apart; the front end surface of the stop ring is tightly combined with the high pressure turbine rotor; rubber sealing rings are arranged between the stop ring and the outer cover and between the rear thrust ring and the outer cover;

[0008] a plurality of groups of graphite ring assemblies, which are sleeved on the outer cover and are provided with intermediate rings between adjacent graphite ring assemblies;

[0009] The graphite ring assembly comprises a front sealing ring, a rear sealing ring and an elastic member arranged between the front sealing ring and the rear sealing ring, and the elastic member is used to form an axial thrust on the front sealing ring and the rear sealing ring;

[0010] The front end surface of the front sealing ring of each group of graphite ring assemblies is sealingly combined with the rear end surface of the stop ring or the intermediate ring; and the rear end surface of the rear sealing ring is sealingly combined with the front end surface of the intermediate ring or the rear thrust ring;

[0011] The outer circumferential surface of the front sealing ring and the rear sealing ring is sealingly combined with the inner circumferential surface of the low pressure turbine rotor; and the front sealing ring and the rear sealing ring are respectively provided with openings to form an open ring structure.

[0012] Preferably, thrust bushings are arranged between the stop ring and the intermediate ring, between the intermediate ring and the rear thrust ring, and between two adjacent intermediate rings.

[0013] Preferably, there is a gap between the inner circumferential surface of the front seal ring and the outer circumferential surface of the thrust bushing, and an annular cavity is formed.

[0014] Preferably, a circumferential gas ring groove and a plurality of axial gas guide grooves are arranged on the outer circumferential surface of the front seal ring and the rear seal ring, respectively; the circumferential gas ring groove is arranged circumferentially, and the axial gas guide grooves are arranged axially and extend from the front end surface of the front seal ring and the rear seal ring to the circumferential gas ring groove, respectively; an end surface gas ring groove and a plurality of radial gas guide grooves are arranged on the front end surface of the front seal ring and the rear end surface of the rear seal ring, respectively; the radial gas guide grooves are arranged radially and communicate the annular cavity with the end surface gas ring groove.

[0015] Preferably, the graphite ring assembly further comprises a sleeve and a spacer ring, the elastic member is an end surface spring, and the end surface spring is a wave spring; the sleeve is arranged between the elastic member and the front seal ring; the spacer ring is arranged between the elastic member and the rear seal ring; the two end surfaces of the elastic member abut against the sleeve and the spacer ring, respectively; the sleeve is an annular member with an "L"-shaped cross section, and an annular accommodation cavity is formed between the sleeve and the spacer ring, in which the elastic member is arranged; a limiting ring groove is arranged on the front end surface of the spacer ring; the rear end of the sleeve is inserted into the limiting ring groove.

[0016] Preferably, the rear seal ring is an annular member with an "L"-shaped cross section, and an annular space is formed between the rear seal ring and the front seal ring for accommodating the sleeve, the elastic member, and the spacer ring.

[0017] Preferably, an annular groove is arranged on the outer circumferential surface of the stop ring and forms a gas ring cavity together with the inner circumferential surface of the low-pressure turbine rotor, and the gas ring cavity communicates with the air cavity of the engine; an annular groove is arranged on the outer circumferential surface of the rear thrust ring and forms a pressure ring cavity together with the inner circumferential surface of the low-pressure turbine rotor, and the pressure ring cavity communicates with the oil cavity of the engine.

[0018] Preferably, an annular groove is arranged on the outer circumferential surface of the intermediate ring.

[0019] Preferably, a sealing ring accommodating annular groove is arranged on the inner circumferential surface of the stop ring and the rear thrust ring, respectively, for accommodating the rubber sealing ring.

[0020] Preferably, a bushing is sleeved at the rear end of the outer cover, and the front end surface of the bushing abuts against the rear end surface of the rear thrust ring; a plurality of through holes are uniformly distributed on the circumference of the bushing, and a pin is arranged in the through hole, the inner end of the pin passes through the outer cover and is clamped in the key groove of the high-pressure turbine rotor; a bearing nut is arranged at the rear end of the high-pressure turbine rotor; the front end surface of the bearing nut flower is axially pressed against the bushing; the thin edge at the rear end of the bushing is closed and clamped into the flower groove of the bearing nut; and the oil flow path holes with radial angles are uniformly distributed on the rear end of the bushing.

[0021] Due to the adoption of the above technical scheme, the application has the following beneficial effects:

[0022] (1) The application sets multiple groups of graphite ring assemblies, and each group of graphite ring assemblies comprises a front sealing ring, a rear sealing ring and an elastic member; the sealing surface of the front sealing ring is the front end surface and the outer circumferential surface; and the sealing surface of the rear sealing ring is the rear end surface and the outer circumferential surface. During operation, under the high-speed rotating state, since the front sealing ring and the rear sealing ring are both open ring structures, the tension of the formed open ring and the centrifugal force generated by high-speed rotation ensure that the outer circumferential surfaces of the front sealing ring and the rear sealing ring are tightly attached to the inner circumferential surface of the low-pressure turbine rotor, thereby forming a cooperative sealing. Meanwhile, under the action of the elastic member, the axial force generated by the elastic member acts on the front sealing ring and the rear sealing ring, so that the front end surface of the front sealing ring and the rear end surface of the rear sealing ring form end surface sealing correspondingly, and the rubber sealing ring arranged between the stop ring and the outer cover and between the rear thrust ring and the outer cover cooperatively form the sealing structure of the oil cavity between the rotors of the aero-engine.

[0023] (2) The graphite sealing structure for sealing the oil cavity between the rotors of the aero-engine provided by the application can stably and effectively work under the conditions of a maximum high-pressure rotating speed of 15000r / min, a maximum low-pressure rotating speed of 11000r / min, a maximum temperature of 300℃, a pressure difference of (80-160)kPa and a vibration value of 40mm / s, and can realize effective sealing between the oil cavity and the air cavity. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only show some embodiments of the application, and for those skilled in the art, other drawings can also be obtained from the structures shown in the drawings without creative labor.

[0025] Figure 1 A schematic view of the graphite sealing structure for sealing the oil cavity between the rotors of the aero-engine provided by the application;

[0026] Figure 2It is the assembly structure schematic view of graphite ring assembly in the application;

[0027] Figure 3 It is the structure schematic view of front seal ring in the application;

[0028] Figure 4 It is the structure schematic view of front seal ring in the application; Figure 3 It is the enlarged view of M in the middle;

[0029] Figure 5 It is the enlarged view of M in the middle; Figure 3 It is the enlarged view of N in the middle;

[0030] Figure 6 It is the structure schematic view of rear seal ring in the application;

[0031] Figure 7 It is the structure schematic view of rear seal ring in the application; Figure 6 It is the enlarged view of F in the middle;

[0032] Figure 8 It is the perspective view of graphite sealing structure for sealing oil cavity between rotors of aero-engine provided by the application after removing low-pressure turbine rotor.

[0033] Brief Description of the Drawings: 100, graphite ring assembly; 1, thrust bushing; 2, front seal ring; 3, rear seal ring; 4, rubber seal ring; 5, grommet; 5-1, limiting ring groove; 6, sleeve; 7, intermediate ring; 8, pin; 9, elastic member; 10, stop ring; 11, bushing; 11-1, oil flow path hole; 12, outer cover; 13, rear thrust ring; 14, high-pressure turbine rotor; 15, low-pressure turbine rotor; 16, bearing nut; 17, annular cavity; 18, peripheral surface gas collecting ring groove; 19, axial gas guide groove; 20, end surface gas collecting ring groove; 21, radial gas guide groove; 22, opening; 23, gas collecting ring cavity; 24, pressure ring cavity. DETAILED DESCRIPTION

[0034] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the application.

[0035] It should be noted that all directionality indications (such as up, down, left, right, front, back, etc.) in the embodiments of the application are only used to explain the relative position relationship, movement condition, etc. between components in a certain specific posture (as shown in the drawings), and if the specific posture changes, the directionality indications also change accordingly.

[0036] In addition, in the embodiment, the end face of each component close to the air cavity is a front end face, and the end face close to the oil cavity is a rear end face.

[0037] In combination Figure 1 , Figure 2 The graphite sealing structure for sealing the inter-rotor oil cavity of an aero-engine includes a high-pressure turbine rotor 14 and a low-pressure turbine rotor 15, and is characterized in that it further includes:

[0038] An outer cover 12 is sleeved on the high-pressure turbine rotor 14; a stop ring 10 and a rear thrust ring 13 are sleeved on the outer cover 12 and are spaced apart; the front end face of the stop ring 10 is tightly combined with the high-pressure turbine rotor 14 to form an end face seal; a rubber sealing ring 4 is arranged between the stop ring 10 and the outer cover 12 and between the rear thrust ring 13 and the outer cover 12; a plurality of graphite ring assemblies 100 are sleeved on the outer cover 12, and an intermediate ring 7 is arranged between adjacent graphite ring assemblies 100; the graphite ring assembly 100 includes a front sealing ring 2, a rear sealing ring 3, and an elastic member 9 arranged between the front sealing ring 2 and the rear sealing ring 3, which is used to form an axial thrust on the front sealing ring 2 and the rear sealing ring 3; the front end face of the front sealing ring 2 of each graphite ring assembly 100 is in sealing cooperation with the rear end face of the stop ring 10 or the intermediate ring 7; the rear end face of the rear sealing ring 3 is in sealing cooperation with the front end face of the intermediate ring 7 or the rear thrust ring 13; the outer circumferential surface of the front sealing ring 2 and the rear sealing ring 3 is in sealing cooperation with the inner circumferential surface of the low-pressure turbine rotor 15;

[0039] In combination Figure 4 , Figure 7 As shown, the front sealing ring 2 and the rear sealing ring 3 are respectively provided with openings 22 to form an open ring structure; in the embodiment, the gap width of the opening 22 is between 10 μm and 50 μm after the front sealing ring 2 and the rear sealing ring 3 are assembled.

[0040] In combination Figure 1 , Figure 2As shown, the sealing surface of the front seal ring 2 is the front end surface and the outer peripheral surface; the sealing surface of the rear seal ring 3 is the rear end surface and the outer peripheral surface. In operation, under high-speed rotation, since the front seal ring 2 and the rear seal ring 3 are both open ring structures, the tension of the open ring formed and the centrifugal force generated by high-speed rotation ensure that the outer peripheral surfaces of the front seal ring 2 and the rear seal ring 3 are tightly attached to the inner peripheral surface of the low-pressure turbine rotor 15, forming a matching seal. At the same time, under the action of the elastic member 9, the axial force generated by the elastic member 9 acts on the front seal ring 2 and the rear seal ring 3, so that the front end surface of the front seal ring 2 and the rear end surface of the rear seal ring 3 form an end surface seal accordingly, and at the same time, the rubber seal ring 4 arranged between the stop ring 10, the rear thrust ring 13 and the outer cover 12 cooperates to form a sealing structure of the oil cavity between the turbine rotors of the aero-engine. In addition, two sets of graphite ring assemblies 100 are arranged in this embodiment, and the combination of the two sets of graphite ring assemblies 100 increases the sealing surface, which can further ensure the sealing reliability and effect. The number of graphite ring assemblies 100 can be set according to the length and size of the high-pressure turbine rotor 14 and the low-pressure turbine rotor 15 and the sealing requirement, and a multi-stage arrangement combination mode is formed, and the number is not limited to Figure 1 two sets as shown.

[0041] In combination Figure 1 , Figure 2 As shown, the thrust bushing 1 is arranged between the stop ring 10 and the intermediate ring 7, between the intermediate ring 7 and the rear thrust ring 13, and between adjacent two intermediate rings 7. The thrust bushing 1 has a certain axial length, and forms a fixed range between the stop ring 10 and the intermediate ring 7, between the intermediate ring 7 and the rear thrust ring 13, and between adjacent two intermediate rings 7, to ensure the axial working space of the graphite ring assembly 100, and the inner circle of the thrust bushing 1 is attached to the outer circle of the outer cover 12.

[0042] In combination Figure 2 As shown, there is a gap between the inner peripheral surface of the front seal ring 2 and the rear seal ring 3 and the outer peripheral surface of the thrust bushing 1, and an annular cavity 17 is formed. When rotating at high speed, the centrifugal force generated by the change of the rotating speed on the front seal ring 2 and the rear seal ring 3 is variable, and since the front seal ring 2 and the rear seal ring 3 are open ring structures, the front seal ring 2 and the rear seal ring 3 will form a certain opening or closing in the radial direction, and the engine will vibrate to a certain extent when working, and the rotor will have a certain amplitude in the radial direction, which will also cause the front seal ring 2 and the rear seal ring 3 to form a certain opening and closing in the radial direction. By arranging the annular cavity 17 structure, a buffer zone for the radial movement of the front and rear seal rings in operation is formed; in addition, the annular cavity 17 also has the function of gas collection and pressure stabilization.

[0043] In combination Figure 2 , Figure 4 and Figure 7As shown, the outer circumferential surface of the front seal ring 2 and the rear seal ring 3 is respectively provided with a circumferential gas collecting groove 18 and a plurality of axial gas guide grooves 19; the circumferential gas collecting groove 18 is circumferentially arranged, and the axial gas guide grooves 19 are axially arranged and respectively extend from the front end surface of the front seal ring 2 and the rear end surface of the rear seal ring 3 to the circumferential gas collecting groove 18; the front end surface of the front seal ring 2 and the rear end surface of the rear seal ring 3 are respectively provided with an end surface gas collecting groove 20 and a plurality of radial gas guide grooves 21, and the radial gas guide grooves 21 are radially arranged and communicate the annular cavity 17 with the end surface gas collecting groove 20.

[0044] By arranging the circumferential gas collecting groove 18 and the axial gas guide groove 19 on the front and rear seal rings, the front and rear seal rings are circumferentially sealed with the low-pressure turbine rotor 15 while reducing the contact area; the axial gas guide groove 19 of the front seal ring 2 can guide the gas in the air cavity into the circumferential gas collecting groove 18 of the front seal ring 2, and the axial gas guide groove 19 of the rear seal ring 3 can guide the gas between the front and rear seal rings into the circumferential gas collecting groove 18 of the rear seal ring 3, thereby forming a gas film at the outer circle of the front and rear seal rings, reducing graphite wear, and the circumferential gas collecting groove 18 has the functions of collecting graphite residues and wear.

[0045] By arranging the end surface gas collecting groove 20 and the radial gas guide groove 21 on the front and rear seal rings, the front and rear seal rings can form corresponding end surface sealing surfaces while reducing the contact area; the air in the annular cavity 17 can enter the end surface gas collecting groove 20 through the radial gas guide groove 21, thereby forming a gas film at the end surface, reducing graphite wear, and the end surface gas collecting groove 20 has the functions of collecting graphite residues and wear.

[0046] In combination Figure 2 As shown, the graphite ring assembly 100 further comprises a sleeve 6 and a spacer ring 5, the elastic member 9 is an end surface spring which is a wave spring; the sleeve 6 is arranged between the elastic member 9 and the front seal ring 2; the spacer ring 5 is arranged between the elastic member 9 and the rear seal ring 3; the two end surfaces of the elastic member 9 abut against the sleeve 6 and the spacer ring 5 respectively; by arranging the sleeve 6 and the spacer ring 5, the front and rear seal rings are fully contacted with the end surfaces, so that the elastic force borne by the front and rear seal rings is uniformly distributed in the circumferential direction, thereby avoiding that the wave spring directly abuts against and locally contacts the front and rear seal rings, causing the front and rear seal rings to be damaged due to uneven force in the circumferential direction. The axial force of the elastic member 9 can ensure that the end surface sealing surfaces of the front and rear seal rings are effectively attached.

[0047] The sleeve 6 is an annular member with a cross-section in the shape of "L", and the annular space between the sleeve 6 and the gasket ring 5 is used to accommodate the elastic member 9, which is convenient for installing the elastic member 9; a limiting ring groove 5-1 is arranged on the front end surface of the gasket ring 5; and the rear end of the sleeve 6 is inserted into the limiting ring groove 5-1. By arranging the limiting ring groove 5-1, the width of the annular space formed can be limited during assembly and use, so as to avoid excessive compression of the elastic member 9.

[0048] The elastic member 9 will be compressed to a certain extent during assembly, that is, the wave spring will be compressed to a certain extent by assembly pressure; and during work, a certain axial pressure will be generated under the condition that there is a certain pressure difference between the air cavity and the lubricating oil cavity, and the axial pressure will also be transmitted to the wave spring, so that the wave spring is further compressed. In this way, the wave spring will provide a certain amount of elastic force to the front and rear sealing rings, so as to ensure that an end surface sealing surface of the front and rear sealing rings is always in a state of adhesion, thereby forming an effective end surface sealing.

[0049] As shown in the combination Figure 2 The rear sealing ring 3 is an annular member with a cross-section in the shape of "L", and the annular space between the rear sealing ring 3 and the front sealing ring 2 is used to accommodate the sleeve 6, the elastic member 9, and the gasket ring 5. Through this structure, the installation of the sleeve 6, the elastic member 9, and the gasket ring 5 is facilitated.

[0050] As shown in the combination Figure 1 As shown in the combination, an annular groove is arranged on the outer circumferential surface of the stop ring 10 and cooperates with the inner circumferential surface of the low-pressure turbine rotor 15 to form a gas collecting ring cavity 23, and the gas collecting ring cavity 23 is in communication with the air cavity of the engine; the gas collecting ring cavity 23 can play a role of stabilizing pressure.

[0051] As shown in the combination Figure 1 As shown in the combination, an annular groove is arranged on the outer circumferential surface of the rear thrust ring 13 and cooperates with the inner circumferential surface of the low-pressure turbine rotor 15 to form a pressure ring cavity 24, and the pressure ring cavity 24 is in communication with the lubricating oil cavity of the engine. The pressure ring cavity 24 has the function of stabilizing pressure. The front end surface of the rear thrust ring 13 is in end surface sealing with the rear sealing ring 3.

[0052] As shown in the combination Figure 1 As shown in the combination, an annular groove is arranged on the outer circumferential surface of the intermediate ring 7. The annular groove on the outer circumferential surface of the intermediate ring 7 has the functions of gas collecting and pressure stabilizing, and collecting graphite residues, wear and other residues. The intermediate ring 7 has the function of separating the two-stage graphite ring assembly 100, and the front and rear end surfaces of the intermediate ring 7 are in end surface sealing with the front and rear sealing rings. The inner circle of the intermediate ring 7 is in abutment with the outer circle of the outer cover 12.

[0053] As shown in the combination Figure 1 As shown in the combination, a sealing ring accommodating annular groove is arranged on the inner circumferential surface of the stop ring 10 and the rear thrust ring 13 respectively, which is used to accommodate the rubber sealing ring 4.

[0054] As shown in the combinationFigure 1 As shown, the rear end of the outer cover 12 is sleeved with a bushing 11, and the front end surface of the bushing 11 abuts against the rear end surface of the rear thrust ring 13; a plurality of through holes are uniformly distributed on the circumference of the bushing 11, and a pin 8 is arranged in the through hole, the inner end of the pin 8 passes through the outer cover 12 and is clamped in the key groove of the high-pressure turbine rotor 14, thereby limiting the circumferential movement of the outer cover 12; the rear end of the high-pressure turbine rotor 14 is provided with a bearing nut 16; the front end surface of the bearing nut 16 is axially pressed against the bushing 11, and the bearing nut 16 limits the axial movement of the components on the outer cover 12; the thin edge at the rear end of the bushing 11 is closed and clamped into the flower edge groove of the bearing nut 16, thereby limiting the circumferential movement of the bearing nut 16. Radial angle oil flow path holes 11-1 are uniformly distributed on the rear end of the bushing 11, which are used to discharge the oil in the oil passage at the bottom of the outer cover 12 assembly.

[0055] In combination Figure 1 As shown, the outer cover 12 is a thin-walled barrel-shaped part with an L-shaped cross section, and the mounting edge at the front end is axially assembled with the stop ring 10, the thrust bushing 1, the intermediate ring 7, the thrust bushing 1, the thrust ring 13, and the bushing 11 in sequence, and is axially fixed into an assembly at the bushing 11 through the pin 8. The inner circle of the outer cover 12 forms a space with the high-pressure turbine rotor 14 as an oil flow path, which is used for heat dissipation of the entire assembly and the rotor. The outer circle of the outer cover 12 is sealed by rubber sealing rings between the stop ring 10 and the thrust ring 13, thereby ensuring the pressure stability of the graphite sealing structure.

[0056] The above only describes the preferred embodiments of the present application, and does not limit the patent scope of the present application. Any equivalent structural transformation, direct / indirect application in other related technical fields, or the like within the inventive concept of the present application and the content of the specification and drawings are included in the patent protection scope of the present application.

Claims

1. A graphite seal structure for sealing an inter-rotor oil cavity of an aeroengine, comprising a high pressure turbine rotor (14) and a low pressure turbine rotor (15), characterized in that, Also include: Cover (12), set on the high-pressure turbine rotor (14); Stop ring (10) and rear thrust ring (13), both set on the cover (12), and spaced apart; the front end face of the stop ring (10) is closely combined with the high-pressure turbine rotor (14); rubber sealing ring (4) is arranged between the stop ring (10) and the cover (12), and between the rear thrust ring (13) and the cover (12); A plurality of graphite ring assemblies (100) are set on the cover (12), and intermediate rings (7) are arranged between adjacent graphite ring assemblies (100); The graphite ring assembly (100) comprises a front sealing ring (2), a rear sealing ring (3), and an elastic member (9) arranged between the front sealing ring (2) and the rear sealing ring (3), which is used to form an axial thrust on the front sealing ring (2) and the rear sealing ring (3); The front end face of the front sealing ring (2) of each group of graphite ring assemblies (100) is matched and sealed with the rear end face of the stop ring (10) or the intermediate ring (7); the rear end face of the rear sealing ring (3) is matched and sealed with the front end face of the intermediate ring (7) or the rear thrust ring (13); The outer circumferential surface of the front sealing ring (2) and the rear sealing ring (3) is matched and sealed with the inner circumferential surface of the low-pressure turbine rotor (15); the front sealing ring (2) and the rear sealing ring (3) are respectively provided with openings (22) to form an open ring structure; An annular groove is arranged on the outer circumferential surface of the stop ring (10) and forms a gas collecting ring cavity (23) with the inner circumferential surface of the low-pressure turbine rotor (15), and the gas collecting ring cavity (23) is communicated with the air cavity of the engine; an annular groove is arranged on the outer circumferential surface of the rear thrust ring (13) and forms a pressure ring cavity (24) with the inner circumferential surface of the low-pressure turbine rotor (15), and the pressure ring cavity (24) is communicated with the oil cavity of the engine.

2. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as set forth in claim 1, wherein, A thrust bushing (1) is arranged between the stop ring (10) and the intermediate ring (7), between the intermediate ring (7) and the rear thrust ring (13), and between two adjacent intermediate rings (7).

3. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as set forth in claim 2, wherein, There is a gap between the inner circumferential surface of the front sealing ring (2) and the rear sealing ring (3) and the outer circumferential surface of the thrust bushing (1) to form an annular cavity (17).

4. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as set forth in claim 3, wherein, A circumferential gas collecting ring groove (18) and a plurality of axial gas guide grooves (19) are respectively arranged on the outer circumferential surface of the front sealing ring (2) and the rear sealing ring (3); the circumferential gas collecting ring groove (18) is arranged in the circumferential direction, and the axial gas guide grooves (19) are arranged in the axial direction and respectively extend from the front end face of the front sealing ring (2) and the rear sealing ring (3) to the circumferential gas collecting ring groove (18); An end face gas collecting ring groove (20) and a plurality of radial gas guide grooves (21) are respectively arranged on the front end face of the front sealing ring (2) and the rear end face of the rear sealing ring (3); the radial gas guide grooves (21) are arranged in the radial direction and communicate the annular cavity (17) with the end face gas collecting ring groove (20).

5. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as defined in claim 1, wherein, The graphite ring assembly (100) further comprises a sleeve (6) and a gasket ring (5), the elastic member (9) is an end face spring which is a wave spring; the sleeve (6) is arranged between the elastic member (9) and the front sealing ring (2); the gasket ring (5) is arranged between the elastic member (9) and the rear sealing ring (3); the two end faces of the elastic member (9) are respectively abutted on the sleeve (6) and the gasket ring (5); The sleeve (6) is an annular member with an "L" shaped cross section, an annular accommodating cavity is formed between the sleeve (6) and the gasket ring (5), and the elastic member (9) is arranged in the annular accommodating cavity; a limiting ring groove (5-1) is arranged on the front end face of the gasket ring (5); the rear end of the sleeve (6) is inserted into the limiting ring groove (5-1).

6. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as set forth in claim 5, characterized in that, The rear sealing ring (3) is an annular member with an "L" shaped cross section, and an annular space is formed between the rear sealing ring (3) and the front sealing ring (2) for accommodating the sleeve (6), the elastic member (9) and the gasket ring (5).

7. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as defined in claim 1, wherein, An annular groove is arranged on the outer circumferential surface of the middle ring (7).

8. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as defined in claim 1, wherein, A sealing ring accommodating annular groove is arranged on the inner circumferential surface of the stop ring (10) and the rear thrust ring (13) respectively for accommodating the rubber sealing ring (4).

9. A graphite seal for sealing an inter-rotor oil cavity of an aircraft engine as defined in claim 1, wherein, A bushing (11) is sleeved on the rear end of the outer cover (12), and the front end face of the bushing (11) abuts on the rear end face of the rear thrust ring (13); a plurality of through holes are uniformly distributed on the circumference of the bushing (11), and a pin (8) is arranged in the through hole, the inner end of the pin (8) passes through the outer cover (12) and is clamped in the key groove of the high-pressure turbine rotor (14); A bearing nut (16) is arranged on the rear end of the high-pressure turbine rotor (14); the front end face of the bearing nut (16) is axially pressed against the bushing (11); the thin edge of the rear end of the bushing (11) is closed and clamped into the flower edge groove of the bearing nut (16); Radial angle oil flow path holes (11-1) are uniformly distributed on the rear end of the bushing (11).

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