Flow guide sealing assembly, turbine disc assembly and engine

Abstract

The invention relates to the technical field of aero-engines, in particular to a flow guide sealing assembly, a turbine disc assembly and an engine. The flow guiding and sealing assembly comprises a stator casing, the stator bearing seat is in butt joint with the bearing seat of the high-pressure rotor to form a bearing cavity for accommodating a bearing; the first sealing mechanism is fixedly connected with the stator casing, arranged on the outer side of the first axial end of the stator bearing seat and used for being in butt joint with the high-pressure rotor; the second sealing mechanism is fixedly connected with the stator casing, arranged on the outer side of the second axial end of the stator bearing seat and used for being in butt joint with the low-pressure rotor; and the flow guide plate assembly is fixed to the stator casing, arranged in the peripheral cavity and used for reducing gas flowing to the bearing cavity from the side, back on to the bearing cavity, of the flow guide plate assembly. The temperature of air outside a bearing cavity can be kept stable, and the running safety of an engine is guaranteed; meanwhile, gas sealing of a bearing cavity and a peripheral cavity is achieved, gas leakage is reduced, the structure is simple, and the sealing effect is good.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aviation engines, and in particular to a guide seal assembly, a turbine disc assembly and an engine. Background Art

[0002] The bearing cavity of an aircraft engine is a component and assembly including bearings, bearing seats, seals, oil supply, oil return, ventilation, etc. In order to ensure the safe operation of the bearing, it is necessary to supply lubricating oil to the bearing cavity. Considering that the boundary of the bearing cavity is the rotating and static interface, there is a leakage gap. The outer cavity of the bearing cavity is a chamber outside the bearing cavity. In order to ensure the safe operation of the bearing in the bearing cavity, and then to ensure the safety and economic operation of the aircraft engine, certain requirements are put forward for the outer sealing cavity of the bearing cavity: on the one hand, to prevent lubricating oil leakage, the pressure of the outer cavity of the bearing cavity is required to be greater than the pressure in the bearing cavity, and a certain pressure difference is maintained, that is, the bearing cavity sealing pressure difference limit; on the other hand, the ignition point of the lubricating oil is low. In order to prevent the lubricating oil from deflagration, it is required that the sealing airflow from the outer cavity of the bearing cavity into the bearing cavity shall not exceed the limit value, that is, the bearing cavity sealing airflow temperature limit. At present, there are the following problems for the sealing of aircraft engines: the sealing airflow needs to flow through high-temperature rotating parts, the wind resistance temperature rise and heat exchange temperature rise along the way are high, the airflow temperature reaching the bearing cavity seal is high, the margin of the distance limit value is small, and overheating problems are prone to occur, resulting in lubricating oil explosion and low safety. Summary of the invention

[0003] To overcome the problems existing in the related art, exemplary embodiments of the present disclosure provide a flow guide seal assembly, a turbine disk assembly and an engine.

[0004] An exemplary embodiment of the first aspect of the present disclosure provides a guide sealing assembly for forming a peripheral cavity of a bearing cavity with a high-pressure rotor and a low-pressure rotor of an engine. The guide sealing assembly may include: a stator casing; a stator bearing seat, fixedly connected to the stator casing, and connected to the bearing seat of the high-pressure rotor to form a bearing cavity for accommodating a bearing; a first sealing mechanism, fixedly connected to the stator casing, disposed on the outer side of a first axial end of the stator bearing seat, and used to dock with the high-pressure rotor to form a gas seal in the peripheral cavity; a second sealing mechanism, fixedly connected to the stator casing, disposed on the outer side of a second axial end of the stator bearing seat, and used to dock with the low-pressure rotor to form a gas seal in the peripheral cavity; a guide plate assembly, the guide plate assembly is fixed to the stator casing, and is disposed in the peripheral cavity to reduce the flow of gas from the side of the guide plate assembly facing away from the bearing cavity to the bearing cavity.

[0005] In some embodiments, the guide plate assembly may include: a first guide plate, one end of which is fixed to the stator casing, extends toward the high-pressure rotor, and is located between the first sealing mechanism and the stator bearing seat.

[0006] In some embodiments, one end of the first deflector plate away from the stator casing can be bent towards the first sealing mechanism, and the gas on the side of the first deflector plate facing away from the stator bearing housing forms a vortex at the bent portion, hindering the gas from flowing towards the stator bearing housing.

[0007] In some embodiments, one or more flow-blocking plates facing the first sealing mechanism can be formed on the side of the first deflector plate away from the stator casing, hindering the gas from flowing towards the stator bearing housing.

[0008] In some embodiments, the deflector plate assembly may further include: a second deflector plate, one end of the second deflector plate is fixed to the stator casing, extends towards the low-pressure rotor, and is located between the second sealing mechanism and the stator bearing housing.

[0009] In some embodiments, one end of the second deflector plate away from the stator casing can be bent towards the second sealing mechanism; the gas on the side of the second deflector plate facing away from the stator bearing housing forms a vortex at the bent portion, hindering the gas from flowing towards the stator bearing housing.

[0010] In some embodiments, one or more flow-blocking plates facing the second sealing mechanism can be formed on the side of the second deflector plate away from the stator casing, hindering the gas from flowing towards the stator bearing housing.

[0011] In some embodiments, the deflector and sealing assembly includes: an oil supply pipe, which penetrates through the stator bearing housing, one end of the oil supply pipe is arranged in the bearing cavity, and the other end is used to be connected to the lubricating oil system of the engine to supply lubricating oil to the bearing cavity; an oil return pipe, which penetrates through the stator bearing housing, one end of the oil return pipe is arranged in the bearing cavity, and the other end is used to be connected to the lubricating oil system of the engine to recover lubricating oil from the bearing cavity.

[0012] In some embodiments, the deflector and sealing assembly may include: a bearing cavity sealing mechanism, which is arranged at the docking surface between the stator bearing housing and the bearing housing of the high-pressure rotor, and is used to dock with the high-pressure rotor bearing housing to form a gas seal for the bearing cavity.

[0013] In a second aspect, according to some other exemplary embodiments, the present disclosure further provides a turbine disk assembly, wherein the turbine disk assembly may include: the deflector and sealing assembly as in the first aspect; a high-pressure rotor, including: a high-pressure rotor bearing housing, a high-pressure sealing mechanism, the high-pressure sealing mechanism is docked with the first sealing mechanism, the high-pressure rotor is connected to the stator casing, and the high-pressure rotor bearing housing is docked with the stator bearing housing to form a bearing cavity; a low-pressure rotor, including: a low-pressure sealing mechanism, the low-pressure sealing mechanism is docked with the second sealing mechanism, the low-pressure rotor is docked with the stator casing, and the high-pressure rotor, the low-pressure rotor and the stator casing are docked to form an outer cavity; a gas flow path is formed between the low-pressure rotor and the high-pressure rotor, and the gas flow path is communicated with the outer cavity to supply gas to the outer cavity.

[0014] In some embodiments, a unique air inlet is formed on one side of the outer cavity close to the second sealing mechanism.

[0015] In some embodiments, the high-pressure sealing mechanism may be provided with a first labyrinth tooth, which docks with the first sealing mechanism to form a labyrinth seal.

[0016] In some embodiments, the low-pressure sealing mechanism may be provided with a second labyrinth tooth, which docks with the second sealing mechanism to form a labyrinth seal.

[0017] In some embodiments, the high-pressure rotor bearing housing may be provided with a third labyrinth tooth, which docks with the bearing cavity sealing mechanism to form a labyrinth seal.

[0018] In a third aspect, according to some other exemplary embodiments, the present disclosure further provides an engine, which may include: a turbine disk assembly as in the second aspect; a compressor, an air extraction port is provided on the compressor journal and is connected to the gas flow path of the turbine disk assembly, and the gas flows from the air extraction port into the gas flow path of the turbine disk assembly.

[0019] In some embodiments, the compressor may include: a compressor disk cavity channel; one end of the compressor disk cavity channel is connected to the air extraction port on the compressor journal, and the other end is connected to the gas flow path of the turbine disk assembly, and the gas flows from the air extraction port into the compressor disk cavity channel and then enters the gas flow path of the turbine disk assembly.

[0020] The technical solutions provided by the embodiments of the present disclosure may include the following beneficial effects: The diversion and sealing assembly guides the gas away from the engine bearing cavity through the diversion plate assembly provided on the stator bearing housing, effectively blocking the gas formed during the rotation of the high-pressure rotor and the low-pressure rotor, keeping the temperature of the gas outside the bearing cavity stable, and ensuring the safety of the engine operation; at the same time, by setting the sealing mechanism, the gas sealing between the bearing cavity and the peripheral cavity is realized, the sealing pressure difference is maintained, the gas leakage is reduced, the structure is simple, and the sealing effect is good.

[0021] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] By describing the exemplary embodiments of the present disclosure in conjunction with the drawings, the present disclosure can be better understood. In the drawings:

[0023] Figure 1 is a schematic structural diagram of a diversion and sealing assembly shown according to an exemplary embodiment of the present disclosure;

[0024] Figure 2 is a schematic structural diagram of a turbine disk assembly shown according to an exemplary embodiment of the present disclosure;

[0025] Figure 3 is a schematic diagram of the internal gas flow path of a turbine disk assembly shown according to an exemplary embodiment of the present disclosure;

[0026] Figure 4 It is a schematic diagram of an engine structure shown according to an exemplary embodiment disclosed. Detailed implementation manners

[0027] The following will describe the detailed implementation manners of the present disclosure. It should be noted that in the process of the specific description of these implementation manners, for the sake of concise description, it is impossible for this specification to describe all features of the actual implementation manners in detail. It should be understood that in the actual implementation process of any implementation manner, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and these will also change from one implementation manner to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for those of ordinary skill in the art related to the content disclosed in the present disclosure, some design, manufacturing or production changes made on the basis of the technical content disclosed in the present disclosure are only conventional technical means and should not be understood as the content of the present disclosure being insufficient.

[0028] Unless otherwise defined, the technical terms or scientific terms used in the claims and the specification should have the ordinary meaning understood by those of ordinary skill in the art in the technical field to which the present disclosure belongs. The "first", "second" and similar terms used in the specification and claims of the present patent application do not indicate any order, quantity or importance, but are only used to distinguish different components. The terms such as "a" or "an" do not indicate a quantity limitation, but indicate that there is at least one. The terms such as "comprising" or "including" mean that the elements or items appearing before "comprising" or "including" cover the elements or items listed after "comprising" or "including" and their equivalent elements, and do not exclude other elements or items. The terms such as "connected" or "coupled" are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0029] Currently, there are mainly two methods for sealing the bearing cavity of an aeroengine. One is to directly supply the sealing air flow to the peripheral cavity of the bearing cavity through a pipeline. This method requires an additional design of the ventilation flow path in the disk center and isolates the sealing air flow supply pipeline from the ventilation flow path in the disk center. The flow path design is complex and the reliability of the engine is low. The other is to design a bearing cavity sealing flow path in the disk center of the engine and merge it with the ventilation flow path in the disk center. The sealing air flow of this method needs to flow through high-temperature rotating components, and the frictional resistance temperature rise and heat transfer temperature rise along the way are relatively high. The temperature of the air flow reaching the bearing cavity sealing is relatively high, and the margin from the limit value is small, so it is easy to have an over-temperature problem, resulting in lubricating oil explosion and low safety.

[0030] To solve the above technical problems, Figure 1 , 2 As shown in Figure 3, the present disclosure provides a flow guide sealing assembly 100, which is used to form a peripheral cavity 170 of a bearing cavity with a high-pressure rotor 210 and a low-pressure rotor 220 of an engine. The flow guide sealing assembly 100 may include: a stator casing 110, a stator bearing seat 120, a first sealing mechanism 130, a second sealing mechanism 140, and a guide plate assembly. The flow guide sealing assembly 100 has a simple structure, and can achieve gas sealing between the bearing cavity 160 and the peripheral cavity 170, reducing the leakage of gas in the peripheral cavity 170 to the external environment; at the same time, it can prevent high-temperature gas generated by flow resistance temperature rise when the engine is running from flowing to the bearing cavity 160, so that the gas temperature inside and outside the bearing cavity 160 remains stable, thereby improving the safety of the bearing cavity 160 when the engine is working.

[0031] Among them, the stator casing 110 can be a cylindrical shell, and the stator casing 110 can be sleeved on the outside of the engine stator component to provide support and protection for the engine stator component. The stator bearing seat 120 can be connected to the bearing seat of the high-pressure rotor 210 to form a bearing cavity 160 for accommodating the bearing; the stator bearing seat 120 can be fixedly connected to the stator casing 110, and is arranged on the radial inner side of the stator casing 110, for installing the bearing, supporting and fixing the bearing; the stator bearing seat 120 can be annular, and the cross section of the stator bearing seat 120 is U-shaped, and is sleeved on the outer peripheral side of the bearing. The two axial ends of the stator bearing seat 120 can extend outward along the axial direction, and a bearing cavity sealing mechanism connected to the high-pressure rotor bearing seat 211 is provided on the extended part, which is used to seal the bearing cavity 160. The peripheral cavity 170 can be a chamber formed by the high-pressure rotor 210, the low-pressure rotor 220, and the stator casing 110. The bearing cavity 160 is arranged inside the peripheral cavity 170.

[0032] The first sealing mechanism 130 can be fixedly connected to the stator casing 110 and is disposed outside the first end in the axial direction of the stator bearing housing 120 for docking with the high-pressure rotor 210 to form a gas seal for the peripheral cavity 170. The first sealing mechanism 130 can be fixedly arranged at one end of the stator casing 110 facing the engine compressor. The end of the stator bearing housing 120 facing the compressor is the first end of the stator bearing. The first sealing mechanism 130 is located outside the first end in the axial direction of the stator bearing housing 120. The first sealing mechanism 130 can be docked with the high-pressure rotor 210. The first sealing mechanism 130 and the high-pressure rotor 210 can be docked in the form of a gas seal. The first sealing mechanism 130 and the high-pressure rotor 210 can be docked by a labyrinth seal method. The high-pressure rotor 210 can be provided with circumferential sealing labyrinth teeth on the docking surface with the first sealing mechanism 130. The docking surface of the first sealing mechanism 130 can be an annular cylindrical surface and can be correspondingly docked with the sealing labyrinth teeth of the high-pressure rotor 210. The first sealing mechanism 130 and the high-pressure rotor 210 can also be docked by a graphite seal method. The docking surface of the first sealing mechanism 130 can be provided with a graphite ring, and the graphite ring can contact the high-pressure rotor 210 to achieve sealing. When the engine is running, the high-pressure rotor 210 rotates at a high speed, and the gas on the outer peripheral side of the high-pressure rotor 210 generates a flow resistance temperature rise, and the gas temperature increases. The high-temperature gas on the outer peripheral side of the high-pressure rotor 210 can be sealed by the first sealing mechanism 130 in the peripheral cavity 170, reducing the leakage of the gas inside the peripheral cavity 170, improving the engine efficiency, and at the same time being able to ensure the internal air pressure of the peripheral cavity 170, so that the peripheral cavity 170 and the bearing cavity 160 maintain a sealing pressure difference, and effectively preventing the bearing lubricating oil in the bearing cavity 160 from leaking out.

[0033] The second sealing mechanism 140 is fixedly connected to the stator casing 110. One end of the stator bearing housing 120 facing the engine tail nozzle is the second end of the stator bearing. The second sealing mechanism 140 is arranged outside the second end of the stator bearing housing 120 in the axial direction and is used to dock with the low-pressure rotor 220 to form a gas seal for the peripheral cavity 170. The second sealing mechanism 140 and the high-pressure rotor 210 can be docked in the form of a gas seal. The second sealing mechanism 140 and the low-pressure rotor 220 can be docked by means of labyrinth sealing. The low-pressure rotor 220 can be provided with circumferential sealing labyrinth teeth on the docking surface with the second sealing mechanism 140. The docking surface of the second sealing mechanism 140 can be an annular cylindrical surface, which can be correspondingly docked with the sealing labyrinth teeth of the low-pressure rotor 220. The second sealing mechanism 140 and the low-pressure rotor 220 can also be docked by means of graphite sealing. The docking surface of the second sealing mechanism 140 can be provided with a graphite ring, and the graphite ring can contact the low-pressure rotor 220 to achieve sealing. The second sealing mechanism 140 can be docked with the low-pressure rotor 220. When the low-pressure rotor 220 in the engine rotates at a high speed, the high-temperature gas generated by the temperature rise due to flow resistance on the outer peripheral side of the low-pressure rotor 220 can be sealed by the second sealing mechanism 140 in the peripheral cavity 170, reducing the gas leakage inside the peripheral cavity 170, improving the engine efficiency, and at the same time being able to ensure the internal air pressure of the peripheral cavity 170, keeping a sealing pressure difference between the peripheral cavity 170 and the bearing cavity 160, and effectively preventing the bearing lubricating oil in the bearing cavity 160 from leaking out.

[0034] The deflector assembly can be fixed to the stator casing 110 and is arranged in the peripheral cavity 170 to reduce the flow of gas from the side of the deflector assembly facing away from the bearing cavity 160 to the bearing cavity 160. The deflector assembly can be a heat-resistant plate, with one end fixed to the stator casing 110 and the other end extending into the peripheral cavity 170. When the engine is running, the gas flowing into the peripheral cavity 170 has a relatively high temperature. Since there is lubricating oil for lubricating the bearing inside the bearing cavity 160, the lubricating oil is prone to combustion and explosion in a high-temperature environment. Under the action of the deflector assembly, part of the gas can flow along the side of the deflector assembly facing away from the bearing cavity 160, keeping the high-temperature gas generated by the temperature rise due to flow resistance away from the engine bearing cavity 160; it can reduce the flow of high-temperature gas to the bearing cavity 160, keep the gas temperature inside and outside the engine bearing cavity 160 stable, and improve safety.

[0035] The flow guiding and sealing component 100 realizes the gas sealing between the bearing cavity 160 and the peripheral cavity 170 by setting a sealing mechanism, maintains the pressure difference between the peripheral cavity 170 and the external environment, realizes gas sealing, reduces the leakage of the gas in the peripheral cavity 170 to the external environment, and has a simple structure. At the same time, by setting a flow guiding plate component on the stator bearing housing 120, when the engine is running, the gas flowing into the peripheral cavity 170 flows along the side of the flow guiding plate component facing away from the bearing cavity 160, so that the high-temperature gas generated due to the temperature rise caused by flow resistance is far away from the engine bearing cavity 160, effectively blocks the high-temperature gas, prevents the high-temperature gas from flowing into the bearing cavity 160, keeps the gas temperature inside and outside the bearing cavity 160 stable, and improves the safety of the bearing cavity during the operation of the engine.

[0036] In some embodiments, as Figure 1 shown, the flow guiding plate component may include: a first flow guiding plate 151, one end of the first flow guiding plate 151 is fixed to the stator casing 110, extends towards the high-pressure rotor 210, and is located between the first sealing mechanism 130 and the stator bearing housing 120. One end of the first flow guiding plate 151 may be fixed to the stator casing 110, and is provided at the first end of the stator casing 110 in the axial direction. The other end of the first flow guiding plate 151 may extend towards the high-pressure rotor 210 into the peripheral cavity 170. The first flow guiding plate 151 may be an annular plate made of a high-temperature resistant material. When the engine is working, the high-pressure rotor 210 rotates at a high speed, and the gas on the periphery of the high-pressure rotor 210 heats up, which easily causes the lubricating oil inside the bearing cavity 160 to explode. Under the action of the first flow guiding plate 151, part of the high-temperature gas on the periphery of the high-pressure rotor 210 can flow along the first flow guiding plate 151 towards the first sealing mechanism 130, effectively blocking part of the high-temperature gas, preventing the high-temperature gas from flowing into the bearing cavity 160 and causing lubricating oil explosion. At the same time, the high-temperature gas is diverted to the first sealing mechanism 130 through the flow guiding plate, and the high-temperature gas is used for the sealing of the bearing cavity 160 and the peripheral cavity 170, and at the same time maintains the sealing pressure difference between the sealed peripheral cavity 170 and the bearing cavity 160.

[0037] In some embodiments, as Figure 1 、 2As shown in FIGS. 3, one end of the first deflector 151 away from the stator casing 110 can be bent towards the first sealing mechanism 130. The gas on the side of the first deflector 151 facing away from the stator bearing housing 120 forms a vortex at the bent portion, hindering the gas from flowing towards the stator bearing housing 120. One end of the first deflector 151 close to the stator casing 110 can be a straight plate, and one end away from the stator casing 110 can be bent towards the first sealing mechanism 130; the first deflector 151 can also be a curved deflector, and the first deflector 151 can be an arc plate, and one end of the arc plate away from the stator casing 110 is bent towards the first sealing mechanism 130; the high-temperature gas generated due to the flow resistance temperature rise flows from the high-pressure rotor 210 to the first deflector 151, and part of the high-temperature gas flows along the surface of the first deflector 151 on the side facing away from the stator bearing housing 120, flows along the bent portion of the first deflector 151, and circulates along the bent portion of the first deflector 151 and the first sealing mechanism 130 to form a vortex, so that it cannot flow towards the stator bearing housing 120. A small part of the high-temperature gas is affected by the wind resistance heat generated by the rotational disturbance and flows from the first deflector 151 to the first sealing mechanism 130. By providing the bent first deflector 151, it can effectively hinder part of the high-temperature gas from flowing towards the stator bearing housing 120, and at the same time make the gas form a vortex at the bent portion of the first deflector 151, which can effectively adjust the gas flow field distribution in the peripheral cavity 170, maintain the sealing pressure difference of the gas in the peripheral cavity 170, and is beneficial to the sealing of the peripheral cavity 170.

[0038] In some embodiments, one or more flow blocking plates facing the first sealing mechanism 130 can be formed on the side of the first deflector 151 away from the stator casing 110 to hinder the high-temperature gas from flowing towards the stator bearing housing 120. The flow blocking plate can be a Y-shaped plate with two branches. Two or more flow blocking plates can also be provided, and the angles between the multiple flow blocking plates and the first deflector 151 can be different; the angles between the multiple flow blocking plates and the first deflector 151 can be the same and are arranged in parallel on the side of the first deflector 151 away from the stator casing 110. The flow blocking plates can also branch at different positions on the side of the first deflector 151 away from the stator casing 110, and there can be a certain distance between the multiple flow blocking plates; when the engine is running, the high-temperature gas can flow along the multiple flow blocking plates, and a vortex is formed between two adjacent flow blocking plates, effectively blocking the high-temperature gas from flowing towards the stator bearing housing 120. By providing multiple branched flow blocking plates, the high-temperature gas is hindered from flowing towards the stator bearing housing 120, so that the gas near the stator bearing housing 120 remains at a low temperature, effectively improving the safety of the bearing cavity 160 during the operation of the engine. At the same time, by providing multiple flow blocking plates, the gas forms a vortex between the flow blocking plates, which can hinder the gas from leaking to the outside and achieve the sealing effect.

[0039] In some embodiments, such as Figure 1 、 2As shown in Figures 3 and 4, the guide plate assembly may further include: a second guide plate 152, one end of which is fixed to the stator casing 110, extends toward the low-pressure rotor 220, and is located between the second sealing mechanism 140 and the stator bearing seat 120. The second guide plate 152 may be an annular plate made of a high-temperature resistant material, one end of which may be fixedly arranged at the first end of the stator casing 110, and the other end of which extends toward the low-pressure rotor 220. When the engine is working, the low-pressure rotor 220 rotates, and the surrounding gas is heated. Part of the high-temperature gas on the surrounding side of the low-pressure rotor 220 can flow along the second guide plate 152 toward the second sealing mechanism 140, blocking part of the high-temperature gas, effectively preventing the high-temperature gas from flowing to the bearing cavity 160 and causing danger. At the same time, the high-temperature gas is guided to the second sealing mechanism 140 through the guide plate, and the high-temperature gas is used to seal the bearing cavity 160 and the peripheral cavity 170, maintaining the sealing pressure difference between the sealed peripheral cavity 170 and the outside.

[0040] In some embodiments, Figure 1 , 2 As shown in Figures 3 and 4, the end of the second guide plate 152 away from the stator casing 110 can be bent toward the second sealing mechanism 140; the gas on the side of the second guide plate 152 away from the stator bearing seat 120 forms a vortex at the bend, which hinders the gas from flowing toward the stator bearing seat 120. The end of the second guide plate 152 close to the stator casing 110 can be a straight plate, and the end away from the stator casing 110 can be bent toward the second sealing mechanism 140, forming a hook shape. The second guide plate 152 may also be a curved guide plate, with one end of the second guide plate 152 away from the stator casing 110 facing the second sealing mechanism 140. The high-temperature gas flows from the circumference of the low-pressure rotor 220 to the second guide plate 152, and part of the high-temperature gas flows along the surface of the second guide plate 152 away from the stator bearing seat 120, circulates along the curved part of the second guide plate 152 and the first sealing mechanism 130, and forms a vortex, so that it cannot flow to the stator bearing seat 120. Part of the high-temperature gas affected by the wind resistance heat generated by the rotation disturbance flows from the second guide plate 152 to the second sealing mechanism 140. By setting the curved second guide plate 152, part of the high-temperature gas can be effectively blocked from flowing to the stator bearing seat 120, and at the same time, the gas forms a vortex at the curved part of the second guide plate 152, which can effectively adjust the gas flow field distribution of the peripheral cavity 170, maintain the sealing pressure difference of the gas in the peripheral cavity 170, and facilitate the sealing of the peripheral cavity 170.

[0041] In some embodiments, on the side away from the stator casing 110, the second deflector 152 may form one or more baffle plates facing the second sealing mechanism 140 to impede the gas flow towards the stator bearing housing 120. The baffle plate may be a Y-shaped plate with two branches. More than two baffle plates may also be provided, and the angles between the multiple baffle plates and the second deflector 152 may be different; the angles between the multiple baffle plates and the second deflector 152 may be the same, and they may be arranged in parallel on the side of the second deflector 152 away from the stator casing 110. The baffle plates may also branch at different positions on the side of the second deflector 152 away from the stator casing 110, and there may be a certain distance between the multiple baffle plates; when the engine is operating, the high-temperature gas can flow along the multiple baffle plates, forming eddy currents between two adjacent baffle plates, effectively blocking the high-temperature gas from flowing towards the stator bearing housing 120. By providing multiple branched baffle plates to impede the high-temperature gas from flowing towards the stator bearing housing 120, the gas near the stator bearing housing 120 can be kept at a low temperature, effectively improving the safety of the bearing cavity during engine operation. At the same time, by providing multiple baffle plates, eddy currents are formed between the baffle plates, which can impede the gas from leaking to the outside, achieving the sealing of the outer cavity 170 of the bearing cavity.

[0042] In some embodiments, as Figure 2 shown, the diversion and sealing assembly 100 includes: an oil supply pipe and an oil return pipe; the oil supply pipe passes through the stator bearing housing 120, with one end disposed in the bearing cavity 160 and the other end for connection to the engine's lubricating oil system to supply lubricating oil to the bearing cavity 160; the oil return pipe passes through the stator bearing housing, with one end disposed in the bearing cavity 160 and the other end for connection to the engine's lubricating oil system to recover the lubricating oil from the bearing cavity 160. One end of the oil supply pipe is disposed in the bearing cavity 160, and the other end passes through the stator bearing housing 120 and is connected to the engine's lubricating oil system. When the engine is operating, the lubricating oil flows from the lubricating oil system to the oil supply pipe and then into the bearing in the bearing cavity 160 to lubricate the bearing; one end of the oil return pipe is disposed in the bearing cavity 160, and the other end passes through the stator bearing housing 120 and is connected to the engine's lubricating oil system. When the engine is operating, the lubricating oil in the bearing cavity 160 flows along the oil return pipe and towards the engine's lubricating oil system, realizing the recovery and circulation of the lubricating oil. By providing the oil supply pipe and the oil return pipe, the bearing can be continuously lubricated, reducing the friction and wear inside the bearing and extending the service life of the bearing. At the same time, through the oil supply pipe and the oil return pipe, the circulating oil lubrication of the bearing cavity is realized, and the lubricating oil after passing through the bearing is filtered and cooled and then used again, which can achieve the cooling of the bearing in the bearing cavity.

[0043] In some embodiments, the flow guiding and sealing assembly 100 may include: a bearing cavity sealing mechanism; the bearing cavity sealing mechanism is disposed on the mating surface of the stator bearing housing 120 and the high-pressure rotor bearing housing 211, and is used to mate with the high-pressure rotor bearing housing to form a gas seal for the bearing cavity. The bearing cavity sealing mechanism may be disposed on the mating surface of the stator bearing housing 120 and the high-pressure rotor bearing housing 211. The two axial ends of the stator bearing housing 120 may extend axially outward, and a bearing cavity sealing mechanism for mating with the high-pressure rotor bearing housing 211 is disposed on the outward-extending portion for sealing the bearing cavity 160. The bearing cavity sealing mechanism and the high-pressure rotor bearing housing 211 may be mated by a labyrinth seal method. The high-pressure rotor bearing housing 211 may be provided with circumferential sealing labyrinth teeth on the mating surface with the bearing cavity sealing mechanism. The mating surface of the bearing cavity sealing mechanism may be an annular cylindrical surface, which can be correspondingly mated with the sealing labyrinth teeth of the high-pressure rotor bearing housing 211; the bearing cavity sealing mechanism and the high-pressure rotor bearing housing 211 may also be mated by a graphite seal method. A graphite ring may be disposed on the mating surface of the stator bearing housing 120, and the graphite ring may be in contact with the mating surface of the high-pressure rotor bearing housing 211, and can maintain reliable sealing performance under the condition that the high-pressure rotor 210 rotates at a high speed.

[0044] Based on the same inventive concept, the present disclosure also provides a turbine disk assembly 200, as Figure 2 shown, wherein the turbine disk assembly 200 may include: the flow guiding and sealing assembly 100 according to any one of the foregoing embodiments; a high-pressure rotor 210, including: a high-pressure rotor bearing housing 211, a high-pressure sealing mechanism 212, the high-pressure sealing mechanism 212 is mated with the first sealing mechanism 130, the high-pressure rotor 210 is connected to the stator casing 110, and the high-pressure rotor bearing housing 211 is mated with the stator bearing housing 120 to form a bearing cavity 160; a low-pressure rotor 220, including: a low-pressure sealing mechanism 221, the low-pressure sealing mechanism 221 is mated with the second sealing mechanism 140, the low-pressure rotor 220 is mated with the stator casing 110, and the high-pressure rotor 210, the low-pressure rotor 220 and the stator casing 110 are mated to form an outer cavity 170; a gas flow passage 230 is formed between the low-pressure rotor 220 and the high-pressure rotor 210, and the gas flow passage 230 is connected to the outer cavity 170 to supply gas to the outer cavity 170. The high-pressure rotor 210 may include a high-pressure rotor bearing housing 211. The high-pressure rotor bearing housing 211 may be annular, and the cross section of the high-pressure rotor bearing housing 211 is U-shaped and is disposed on the circumferential side of the bearing inner ring. The high-pressure rotor bearing housing 211 may be mated with the stator bearing housing 120 to form a bearing cavity 160 that can accommodate the bearing. The high-pressure rotor bearing housing 211 may be provided with a sealing mechanism on the mating surface with the stator bearing housing 120 for sealing the bearing cavity 160.

[0045] The high-pressure rotor 210 may further include a high-pressure sealing mechanism 212. The high-pressure sealing mechanism 212 is disposed at the docking location between the high-pressure rotor 210 and the stator casing 110. The high-pressure sealing mechanism 212 can be docked with the first sealing mechanism 130 to seal the peripheral cavity 170 and reduce gas leakage. The low-pressure rotor 220 may include a low-pressure sealing mechanism 221. The low-pressure sealing mechanism 221 is disposed at the docking location between the low-pressure rotor 220 and the stator casing 110. The low-pressure sealing mechanism 221 can be docked with the second sealing mechanism 140 to seal the peripheral cavity 170 and reduce gas leakage. The high-pressure rotor 210, the low-pressure rotor 220 and the stator casing 110 are docked to form the peripheral cavity 170. The high-pressure sealing mechanism 212 and the low-pressure sealing mechanism 221 are used to seal the peripheral cavity 170. The gas flow path 230 may be a disk-shaped channel between the high-pressure rotor 210 and the low-pressure rotor 220. The gas flow path 230 is connected to the peripheral cavity 170. The gas flow path 230 may be the only air supply channel for the structure of the peripheral cavity 170. The low-temperature gas led out by the engine compressor can flow through the gas flow path 230 into the peripheral cavity 170, such as Figure 3 shown. The low-temperature gas can flow along the outer sides of the high-pressure rotor bearing housing 211 and the stator bearing housing 120 through the gas flow path 230 to ensure the stability of the gas temperature outside the bearing cavity 160. The low-pressure rotor 220 may be provided with air supply holes for gas circulation. When the low-temperature gas enters the gas flow path 230, the low-temperature gas can flow through the air supply holes to other parts of the engine for cooling and sealing.

[0046] In some embodiments, the peripheral cavity 170 is formed with a unique air intake on the side close to the second sealing mechanism 140. The low-temperature gas led out by the engine compressor can flow through the gas flow path 230 into the peripheral cavity 170, enter the rear part of the peripheral cavity 170 through the unique air intake of the peripheral cavity 170, and flow from the rear part of the peripheral cavity 170 to the front part of the peripheral cavity 170. The low-temperature gas led out by the engine compressor, through the gas flow path 230, flows into the peripheral cavity 170, enters the rear part of the peripheral cavity 170 through the unique air intake on the side of the peripheral cavity 170 close to the second sealing mechanism 140. The low-temperature gas can flow into the peripheral cavity 170 from the rear part of the peripheral cavity 170 and flow along the high-pressure rotor bearing housing 211. The gas first flows through the side of the peripheral cavity 170 close to the second sealing mechanism 140. The gas flows along the outer side of the stator bearing housing 120 to the front part of the peripheral cavity 170 and then to the side of the peripheral cavity 170 close to the first sealing mechanism 130. Through the design of the peripheral cavity 170 and the gas flow path 230, the low-temperature gas can flow from the rear part of the peripheral cavity 170 to the front part of the peripheral cavity 170, making the air flow more uniform and controllable, effectively avoiding the generation of additional eddy currents during gas flow, and making the temperature control of the peripheral cavity 170 simpler and more convenient. At the same time, the peripheral cavity 170 has a unique air intake, and the single air supply structure is more conducive to the guide of the air flow by the deflector assembly, effectively optimizing the internal gas flow field of the peripheral cavity.

[0047] In some embodiments, as Figure 2 shown, the high-pressure sealing mechanism 212 may be provided with a first labyrinth seal, which is docked with the first sealing mechanism 130 to form a labyrinth seal for sealing the gas inside the turbine disk. The high-pressure sealing mechanism 212 may be disposed on the high-pressure rotor 210 at the docking location between the high-pressure rotor 210 and the stator casing 110. The high-pressure sealing mechanism 212 may be docked with the first sealing mechanism 130. The high-pressure sealing mechanism 212 may be provided with first labyrinth seals arranged circumferentially. The first sealing mechanism 130 may be an annular cylindrical surface for docking with the first labyrinth seals. A certain distance may be maintained between the tip of the first labyrinth seal of the first sealing mechanism 130 and the first labyrinth seals of the high-pressure sealing mechanism 212. When the gas flows towards the high-pressure sealing mechanism 212 and the first sealing mechanism 130, it enters the first labyrinth seals through the channel between the tip of the first labyrinth seal and the first sealing mechanism 130, circulates in the gaps between the teeth of the first labyrinth seals to form eddy currents. After passing through multiple tooth gaps, the gas energy is lost, making it difficult for the gas to flow out, thus achieving the sealing effect. The annular cylindrical surface of the first sealing mechanism 130 may also be provided with a honeycomb structure. The part of the annular cylindrical surface of the first sealing mechanism 130 that is docked with the first labyrinth seals may be fixedly connected with a honeycomb sealing ring, which can reduce the distance between the tip of the first labyrinth seal and the first sealing mechanism 130, effectively reduce the gas leakage rate, and ensure the reliability and safety of the engine.

[0048] In some embodiments, as Figure 2 shown, the low-pressure sealing mechanism 221 may be provided with a second labyrinth seal, which is docked with the second sealing mechanism 140 to form a labyrinth seal for sealing the gas inside the turbine disk. The low-pressure sealing mechanism 221 may be disposed on the low-pressure rotor 220 at the docking location between the low-pressure rotor 220 and the stator casing 110. The low-pressure sealing mechanism 221 may be docked with the second sealing mechanism 140. The low-pressure sealing mechanism 221 may be provided with second labyrinth seals arranged circumferentially. The second sealing mechanism 140 may be provided with an annular cylindrical surface for docking with the second labyrinth seals. A certain distance is maintained between the tip of the second labyrinth seal of the second sealing mechanism 140 and the second labyrinth seals of the low-pressure sealing mechanism 221. The gas enters the second labyrinth seals through the channel between the tip of the first labyrinth seal and the second sealing mechanism 140, circulates in the gaps between the teeth of the second labyrinth seals to form eddy currents. After passing through multiple tooth gaps, the gas energy is lost, making it difficult for the gas to flow out, thus achieving the sealing effect. The part of the annular cylindrical surface of the second sealing mechanism 140 that is docked with the second labyrinth seals may be fixedly connected with a honeycomb sealing ring, which can reduce the distance between the tip of the second labyrinth seal and the second sealing mechanism 140, effectively reduce the gas leakage rate, and ensure the reliability and safety of the engine.

[0049] In some embodiments, as Figure 2As shown, the high-pressure rotor bearing housing 211 may be provided with a third labyrinth 240, which is docked with the bearing cavity sealing mechanism to form labyrinth sealing for sealing the bearing cavity. Both axial ends of the high-pressure rotor bearing housing 211 may extend axially outwards, and a sealing mechanism for docking with the stator bearing housing 120 may be provided on the extended part. The sealing mechanism may be a labyrinth sealing mechanism. The docking surface of the high-pressure rotor bearing housing 211 may be provided with circumferentially arranged third labyrinths 240. The bearing cavity sealing mechanism of the stator bearing housing 120 may be set as an annular cylindrical surface for docking with the third labyrinths 240. Through the labyrinth sealing mechanism, the bearing cavity 160 can be sealed, the air pressure difference between the bearing cavity 160 and the peripheral cavity 170 can be maintained, and the internal lubricating oil leakage of the bearing cavity 160 can be prevented.

[0050] Based on the same inventive concept, the present disclosure also provides an engine 300, as Figure 4 shown. Among them, the engine 300 may include: the turbine disk assembly 200 of any of the foregoing embodiments; a compressor 310, an air extraction port 311 is provided on the journal of the compressor 310, which is communicated with the gas flow path 230 of the turbine disk assembly 200, and the gas flows from the air extraction port 311 into the gas flow path 230 of the turbine disk assembly 200 for gas circulation. The engine 300 may further include a combustion chamber 320, which is docked with the compressor 310 for fuel combustion; the engine 300 may further include a turbine 330, one end of which is docked with the combustion chamber 320, and the other end is fixedly connected to the turbine disk assembly 200. The turbine 330 and the turbine disk assembly 200 may be fixed by connecting bolts. An air extraction port 311 may be provided on the journal of the compressor 310 of the engine 300. The air extraction port 311 on the journal of the compressor 310 may be communicated with the gas flow path 230 of the turbine disk assembly 200 for supplying gas to the peripheral cavity 170. The gas may flow out from the air extraction port 311, flow into the gas flow path 230, and enter the peripheral cavity 170 along the gas flow path 230 for cooling, sealing of the bearing cavity 160 and sealing of the peripheral cavity 170. The structure is simple, the air extraction efficiency is high, and the cooling and sealing effects are good.

[0051] In some embodiments, the compressor 300 may include: a compressor disk cavity passage 312; one end of the compressor disk cavity passage 312 is connected to an air extraction port 311 on the journal of the compressor 300, and the other end is connected to the gas flow passage 230 of the turbine disk assembly 200. Gas flows from the air extraction port 311 to the compressor disk cavity passage 312 and then enters the gas flow passage 230 of the turbine disk assembly 200 for gas circulation. The air extraction port 311 on the journal of the compressor 310 can be connected to the compressor disk cavity passage 312 to ventilate and cool the center of the compressor 310 disk. The gas flows out from the air extraction port 311, passes through the compressor disk cavity passage 312, and then flows to the gas flow passage 230 of the turbine disk assembly 200 and enters the peripheral cavity 170 for cooling the bearing cavity 160 and sealing the peripheral cavity 170. It can realize the function of cooling the center of the compressor 310 disk and sealing the bearing cavity 160 with the same air extraction flow path. The flow path design is simple, effectively reducing the air extraction volume of the compressor 310 and improving the engine efficiency.

[0052] This application uses specific terms to describe the embodiments of this application. Such as "one embodiment", "an embodiment", and / or "some embodiments" mean a certain feature, structure, or characteristic related to at least one embodiment of this application. Therefore, it should be emphasized and noted that the "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be combined appropriately.

[0053] In the context of this application, unless the context clearly indicates an exception, words such as "a", "an", "one", and / or "the" are not specifically singular and may also include the plural. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0054] Similarly, it should be noted that, in order to simplify the description of this application disclosure and thus help the understanding of one or more application embodiments, in the previous description of the embodiments of this application, sometimes multiple features are merged into one embodiment, drawing, or description thereof. However, this disclosure method does not mean that the features required by the object of this application are more than those mentioned in the claims. In fact, the features of the embodiment are less than all the features of the single embodiment disclosed above.

[0055] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is only an example and does not constitute a limitation to this application. Although not explicitly stated here, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are proposed in this application, so such modifications, improvements, and corrections still fall within the spirit and scope of the embodiments of this application.

Claims

1. A flow guide seal assembly, used to form a peripheral cavity of a bearing cavity with a high-pressure rotor and a low-pressure rotor of an engine, in, The diversion sealing component comprises: stator casing; A stator bearing seat is fixedly connected to the stator casing and is connected to the bearing seat of the high-pressure rotor to form a bearing cavity for accommodating a bearing; A first sealing mechanism, fixedly connected to the stator casing, disposed outside the first axial end of the stator bearing seat, and used for docking with the high-pressure rotor to form a gas seal of the peripheral cavity; A second sealing mechanism is fixedly connected to the stator casing and is disposed outside the second axial end of the stator bearing seat, and is used to dock with the low-pressure rotor to form a gas seal of the peripheral cavity; A guide plate assembly is fixed to the stator casing and disposed in the peripheral cavity to reduce gas flow from the side of the guide plate assembly facing away from the bearing cavity to the bearing cavity.

2. The guide plate assembly according to claim 1, wherein the guide plate assembly include: A first guide plate, one end of which is fixed to the stator casing, extends toward the high-pressure rotor, and is located between the first sealing mechanism and the stator bearing seat.

3. According to the guide sealing assembly of claim 2, the first guide plate is bent toward the first sealing mechanism at one end away from the stator casing, and the gas on the side of the first guide plate away from the stator bearing seat forms a vortex at the bend, thereby hindering the gas from flowing toward the stator bearing seat.

4. According to the guide sealing assembly of claim 2, the first guide plate forms one or more baffles facing the first sealing mechanism on the side away from the stator casing to prevent gas from flowing toward the stator bearing seat.

5. The guide plate sealing assembly according to any one of claims 1 to 4, wherein the guide plate assembly further comprises: include: A second guide plate, one end of which is fixed to the stator casing, extends toward the low-pressure rotor, and is located between the second sealing mechanism and the stator bearing seat.

6. According to the guide sealing assembly of claim 5, the second guide plate is bent toward the second sealing mechanism at one end away from the stator casing; the gas on the side of the second guide plate away from the stator bearing seat forms a vortex at the bend, thereby hindering the gas from flowing toward the stator bearing seat.

7. The guide sealing assembly according to claim 5, wherein the second guide plate forms one or more baffles facing the second sealing mechanism on a side away from the stator casing to prevent gas from flowing toward the stator bearing seat.

8. The diversion sealing assembly according to claim 1, in, The diversion sealing component comprises: An oil supply pipe is passed through the stator bearing seat, one end of the oil supply pipe is arranged in the bearing cavity, and the other end is used to connect with the lubricating oil system of the engine to supply lubricating oil to the bearing cavity; An oil return pipe is passed through the stator bearing seat, one end of which is arranged in the bearing cavity, and the other end is used to be connected to the lubricating oil system of the engine to recover the lubricating oil from the bearing cavity.

9. The diversion sealing assembly according to claim 1, in, The diversion and sealing assembly includes: a bearing chamber sealing mechanism, which is arranged on the mating surface between the stator bearing housing and the bearing housing of the high-pressure rotor, and is used to mate with the bearing housing of the high-pressure rotor to form a gas seal for the bearing chamber.

10. A turbine disk assembly, wherein, the turbine disk assembly includes: the diversion and sealing assembly according to any one of claims 1-9; a high-pressure rotor, including: a high-pressure rotor bearing housing and a high-pressure sealing mechanism, the high-pressure sealing mechanism is mated with the first sealing mechanism, the high-pressure rotor is connected to the stator casing, and the high-pressure rotor bearing housing is mated with the stator bearing housing to form a bearing chamber; a low-pressure rotor, including: a low-pressure sealing mechanism, the low-pressure sealing mechanism is mated with the second sealing mechanism, the low-pressure rotor is mated with the stator casing, and the high-pressure rotor, the low-pressure rotor and the stator casing are mated to form the peripheral chamber; a gas flow path is formed between the low-pressure rotor and the high-pressure rotor, and the gas flow path is communicated with the peripheral chamber to supply gas to the peripheral chamber.

11. The turbine disk assembly according to claim 10, wherein, the peripheral chamber is formed with a unique air inlet on the side close to the second sealing mechanism.

12. The turbine disk assembly according to claim 10, wherein, the high-pressure sealing mechanism is provided with a first labyrinth tooth, which is mated with the first sealing mechanism to form a labyrinth seal.

13. The turbine disk assembly according to claim 10, wherein, the low-pressure sealing mechanism is provided with a second labyrinth tooth, which is mated with the second sealing mechanism to form a labyrinth seal.

14. The turbine disk assembly according to claim 10, wherein, the high-pressure rotor bearing housing is provided with a third labyrinth tooth, which is mated with the bearing chamber sealing mechanism to form a labyrinth seal.

15. An engine, wherein, the engine includes: the turbine disk assembly according to any one of claims 10-14; a compressor, an air extraction port is arranged on the compressor journal and is communicated with the gas flow path of the turbine disk assembly, and gas flows from the air extraction port into the gas flow path of the turbine disk assembly.

16. The engine according to claim 15, wherein, the compressor includes: a compressor disk cavity passage; one end of the compressor disk cavity passage is communicated with the air extraction port on the compressor journal, and the other end is communicated with the gas flow path of the turbine disk assembly, and gas flows from the air extraction port into the compressor disk cavity passage and then enters the gas flow path of the turbine disk assembly.

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