Bearing cavity sealing air bleed structure and aero-engine

Abstract

This invention discloses a bearing cavity sealing gas induced gas structure, including a sealing ring housing, a bearing housing disposed within the sealing ring housing, a rotating bearing disposed within the bearing housing, a rotor assembly disposed within the sealing ring housing, and a sealing grate ring sleeved outside the rotor assembly. The sealing ring housing and the bearing housing enclose a first cavity, and the sealing ring housing and the sealing grate ring enclose a gas induced gas channel disposed axially opposite to the rotating bearing for introducing sealing gas. An air intake channel is provided between the sealing ring housing and the rotating bearing, which communicates with the first cavity and the gas induced gas channel respectively. The bearing housing includes a second cavity communicating with the inner cavity of the rotating bearing for containing atomized lubricating oil, and a return channel communicating with the first cavity and the second cavity respectively. A guide component is provided at the end of the gas induced gas channel near the rotating bearing for guiding the sealing gas to the air intake channel.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a bearing cavity sealing and bleed air structure. Furthermore, this invention also relates to an aero-engine including the aforementioned bearing cavity sealing and bleed air structure. Background Technology

[0002] The requirements for the lubrication interruption test of an aero-engine are as follows: when the lubrication supply to the main lubrication system is interrupted, the aero-engine can operate at the set power for 30 seconds, and during the lubrication interruption period and the subsequent normal operation period, it will not have an adverse effect on the aero-engine. When the internal bearings are unlubricated, the aero-engine can operate at 75% maximum continuous power for at least 6 minutes. After the internal bearings are restored to lubrication, the aero-engine can operate at 75% maximum continuous power for 30 minutes, and the internal bearings will not seize.

[0003] Currently, to meet the requirements of lubrication interruption tests for aero engines, an emergency lubrication system is usually installed inside the aero engine. Specifically, an emergency oil tank is installed in the oil sump inside the bearing housing to store lubricating oil, and an oil nozzle is installed on top of the emergency oil tank. The oil nozzle includes an oil passage and an air passage. The oil passage is connected to the emergency oil tank, and the air passage is connected to the sealed pressurization chamber of the aero engine. When the main lubrication system supply is interrupted, the lubricating oil in the emergency oil tank is drawn into a mist by the airflow and sprayed into the bearing.

[0004] However, due to the complex structure and limited internal space of aero engines, the additional setup of an emergency lubrication system would greatly increase the design difficulty of the bearing housing and related structures inside the aero engine, and only some bearing housings can meet the installation requirements of the oil tank and lubricating nozzle, resulting in poor applicability. Summary of the Invention

[0005] This invention provides a bearing cavity sealing and bleed air structure and an aero-engine to solve the technical problem that the design of bearing housings and related structures is difficult in existing aero-engines in order to meet the requirements of lubricating oil interruption tests.

[0006] According to one aspect of the present invention, a bearing cavity sealing gas induced gas structure is provided, comprising a sealing ring housing, a bearing housing disposed within the sealing ring housing, a rotating bearing disposed within the bearing housing, a rotor assembly disposed within the sealing ring housing, and a sealing grate ring sleeved outside the rotor assembly. The sealing ring housing and the bearing housing enclose a first cavity, and the sealing ring housing and the sealing grate ring enclose a gas induced gas channel disposed axially opposite to the rotating bearing for introducing sealing gas. An air intake channel is provided between the sealing ring housing and the rotating bearing, which communicates with the first cavity and the gas induced gas channel respectively. The bearing housing includes a second cavity communicating with the inner cavity of the rotating bearing for containing atomized lubricating oil and a return channel communicating with the first cavity and the second cavity respectively. A guide component for guiding the sealing gas to the air intake channel is provided at the end of the gas induced gas channel near the rotating bearing.

[0007] As a further improvement to the above technical solution:

[0008] Furthermore, the sealing ring housing includes a grate sealing part that abuts against the sealing grate ring to prevent lubricating oil from leaking from the air intake channel, and an oil mist separation part that surrounds the rotating bearing to form an air intake channel. The grate sealing part and the oil mist separation part surround the sealing grate ring to form an air intake channel. The oil mist separation part has oil mist separation holes that are respectively connected to the air intake channel and the first cavity in the radial direction.

[0009] Furthermore, multiple oil mist separation holes are provided, and these multiple oil mist separation holes are arranged at intervals along the axial and / or circumferential directions on the oil mist separation section.

[0010] Furthermore, the flow guiding assembly includes a first flow guiding boss formed by the oil mist separation section extending radially toward the sealing grate ring and a second flow guiding boss formed by the sealing grate ring extending radially toward the oil mist separation section. The axial distance between the first flow guiding boss and the rotating bearing is greater than the axial distance between the second flow guiding boss and the rotating bearing.

[0011] Furthermore, the end face of the grate sealing part facing the sealing grate ring is provided with a polishing layer, and the end face of the sealing grate ring facing the grate sealing part is provided with sealing grates that abut against the polishing layer.

[0012] Furthermore, the oil mist separation section has an axial abutment portion on its axial end facing the rotating bearing for axially abutting the rotating bearing to axially position the rotating bearing.

[0013] Furthermore, multiple axial abutment portions are provided, and these multiple axial abutment portions are arranged circumferentially at intervals on the axial end of the oil mist separation portion facing the rotating bearing.

[0014] Furthermore, the rotating bearing includes an outer bearing ring, an inner bearing ring, and a bearing cage disposed between the outer bearing ring and the inner bearing ring. A first opening communicating with a second cavity is provided between the bearing cage and the outer bearing ring, and a second opening communicating with a second cavity is provided between the bearing cage and the inner bearing ring.

[0015] Furthermore, the second cavity is provided with an oil return pool and an oil nozzle for spraying lubricating oil onto the rotating bearing, and the first cavity is provided with an oil return hole communicating with the oil return pool.

[0016] According to another aspect of the present invention, an aircraft engine is also provided, which includes the above-described bearing cavity sealing bleed air structure.

[0017] The present invention has the following beneficial effects:

[0018] The bearing cavity sealing bleed gas structure of this invention, during an oil interruption test of an aero-engine where lubricating oil is no longer supplied to the rotating bearing, allows the sealing gas entering the bleed gas channel to flow into the first container through the intake channel under the guidance of the flow guiding component. This prevents the sealing bleed gas from directly impacting the rotating bearing. The sealing gas then flows into the second cavity through the return channel, causing the gas in the second cavity to flow back, thereby carrying the atomized lubricating oil into the rotating bearing for lubrication. This extends the operating time of the rotating bearing during the oil interruption period, prevents the rotating bearing from seizing, and enables the aero-engine to meet the requirements of the oil interruption test. This solution uses a flow guiding component in the bleed gas channel to guide the sealing gas used to prevent lubricating oil leakage, making full use of the sealing gas to guide the gas in the second cavity to flow back, carrying the atomized lubricating oil to lubricate the rotating bearing. Compared with the prior art, this solution makes subtle and minor modifications to the relevant structures of the bearing housing in the aero-engine, ensuring that the aero-engine meets the requirements of the oil interruption test. It also reduces the design difficulty of the bearing housing and related structures in the aero-engine, is applicable to most aero-engines, has good applicability and practicality, and is suitable for widespread promotion and application.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0021] Figure 1 This is a schematic diagram of the bearing cavity sealing and air duct structure according to a preferred embodiment of the present invention;

[0022] Figure 2This is a simplified structural diagram of the bearing cavity sealing and air duct structure according to a preferred embodiment of the present invention.

[0023] Legend:

[0024] 100. Sealing ring housing; 110. Grate sealing section; 120. Oil mist separation section; 121. First guide boss; 130. Oil mist separation hole; 200. Bearing housing; 210. Second cavity; 220. Lubricating oil nozzle; 300. Rotary bearing; 310. Bearing cage; 320. First opening; 330. Second opening; 400. Rotor assembly; 500. Sealing grate ring; 510. Second guide boss; 600. First cavity; 700. Air intake channel; 800. Air inlet channel; 900. Return channel. Detailed Implementation

[0025] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0026] Figure 1 This is a schematic diagram of the bearing cavity sealing and air duct structure according to a preferred embodiment of the present invention; Figure 2 This is a simplified structural diagram of the bearing cavity sealing and air duct structure according to a preferred embodiment of the present invention.

[0027] like Figure 1 and Figure 2As shown, the bearing cavity sealing and venting structure of this embodiment includes a sealing ring housing 100, a bearing seat 200 disposed within the sealing ring housing 100, a rotating bearing 300 disposed within the bearing seat 200, a rotor assembly 400 disposed within the sealing ring housing 100, and a sealing grate ring 500 sleeved outside the rotor assembly 400. The sealing ring housing 100 and the bearing seat 200 enclose a first cavity 600, and the sealing ring housing 100 and the sealing grate ring 500 enclose a cavity 600 disposed axially opposite to the rotating bearing 300. An air intake channel 800 is provided between the sealing ring housing 100 and the rotating bearing 300, which is connected to the first cavity 600 and the air intake channel 700 respectively. The bearing housing 200 includes a second cavity 210 for containing atomized lubricating oil, which is connected to the inner cavity of the rotating bearing 300, and a return channel 900 that is connected to the first cavity 600 and the second cavity 210 respectively. A guide assembly for guiding the sealing gas to the air intake channel 800 is provided at the end of the air intake channel 700 near the rotating bearing 300. Specifically, in the bearing cavity sealing bleed gas structure of the present invention, when the lubricating oil supply to the rotating bearing 300 is stopped during an oil interruption test of the aero-engine, the sealing gas entering the bleed gas channel 700 flows into the first container through the air intake channel 800 under the guidance of the flow guiding component, to prevent the sealing bleed gas from directly impacting the rotating bearing 300. The sealing gas then flows into the second cavity 210 through the return channel 900, causing the gas in the second cavity 210 to flow back, thereby driving the atomized lubricating oil into the rotating bearing 300 for lubrication. This prolongs the operating time of the rotating bearing 300 during the lubricating oil interruption period, prevents the rotating bearing 300 from seizing, and ensures the smooth operation of the aero-engine. The air-breathing engine meets the requirements of the lubricating oil interruption test. This solution guides the sealing gas used to prevent lubricating oil leakage by setting a flow guide component in the bleed air channel 700. This fully utilizes the sealing gas to guide the gas backflow in the second cavity 210, driving the atomized lubricating oil to lubricate the rotating bearing 300. Compared with the prior art, by making subtle and minor modifications to the relevant structure of the bearing housing 200 in the aero-engine, the aero-engine meets the requirements of the lubricating oil interruption test. Furthermore, the design difficulty of the bearing housing 200 and related structures in the aero-engine is low, and it is applicable to most aero-engines, exhibiting good applicability and practicality, making it suitable for widespread promotion and application. It should be understood that the sealing gas is drawn out from the inner cavity of the rotor assembly 400 and then flows into the bleed air channel 700. Optionally, the rotor assembly 400 is a compressor rotor. It should be understood that the radial, axial, and circumferential directions are all based on the rotor assembly.

[0028] like Figure 1As shown, in this embodiment, the sealing ring housing 100 includes a grate sealing portion 110 that abuts against the sealing grate ring 500 to prevent lubricating oil leakage from the air intake channel 700, and an oil mist separation portion 120 that surrounds the rotating bearing 300 to form an air intake channel 800. The grate sealing portion 110 and the oil mist separation portion 120 surround the sealing grate ring 500 to form the air intake channel 700. The oil mist separation portion 120 has oil mist separation holes 130 that are respectively connected to the air intake channel 700 and the first cavity 600 in the radial direction. Specifically. The sealing part 110 abuts against the sealing ring 500 to further prevent lubricating oil from leaking from the air intake channel 700. The oil mist separator 120 and the rotating bearing 300 form an air intake channel 800 to introduce sealing gas into the first cavity 600. The lubricating oil accumulated in the air intake channel 700 is discharged through the oil mist separator hole 130, so that the lubricating oil in the air intake channel 700 flows into the first cavity 600 under centrifugal force and leaks from the air intake channel 700.

[0029] like Figure 2 As shown, in this embodiment, multiple oil mist separation holes 130 are provided, and the multiple oil mist separation holes 130 are arranged at intervals along the axial and / or circumferential directions on the oil mist separation section 120. Specifically, by arranging multiple oil mist separation holes 130 at intervals along the axial and / or circumferential directions on the oil mist separation section 120, the lubricating oil in the air intake channel 700 is discharged from all directions, thus minimizing lubricating oil leakage.

[0030] like Figure 2 As shown, in this embodiment, the flow guiding assembly includes a first flow guiding boss 121 formed by the oil mist separation section 120 extending radially toward the sealing grate ring 500, and a second flow guiding boss 510 formed by the sealing grate ring 500 extending radially toward the oil mist separation section 120. The axial distance between the first flow guiding boss 121 and the rotating bearing 300 is greater than the axial distance between the second flow guiding boss 510 and the rotating bearing 300. Specifically, the first flow guiding boss 121 and the second flow guiding boss 510 work together to prevent the sealing gas from directly impacting the rotating bearing 300. By making the axial distance between the first flow guiding boss 121 and the rotating bearing 300 greater than the axial distance between the second flow guiding boss 510 and the rotating bearing 300, a flow guiding gap is formed between the first flow guiding boss 121 and the second flow guiding boss 510 toward the air intake channel 800, so as to guide the sealing gas into the first cavity 600 through the air intake channel 800.

[0031] like Figure 1As shown, in this embodiment, the end face of the grate sealing portion 110 facing the sealing grate ring 500 is provided with a wear layer, and the end face of the sealing grate ring 500 facing the grate sealing portion 110 is provided with sealing grates that abut against the wear layer. Specifically, the abutting fit between the sealing grates and the wear layer prevents lubricating oil leakage, and the wear layer reduces the impact wear between the sealing grates and the wear layer. Optionally, the wear layer is made of graphite or aluminum silicon.

[0032] In this embodiment, the oil mist separation section 120 is provided with an axial abutment portion on its axial end facing the rotating bearing 300 for axially abutting the rotating bearing 300 to axially position the rotating bearing 300. Specifically, the axial abutment portion abuts the rotating bearing 300 axially to cooperate with the bearing housing 200 to achieve axial positioning of the rotating bearing 300.

[0033] In this embodiment, multiple axial abutment portions are provided, and these multiple axial abutment portions are arranged circumferentially at intervals on the axial end of the oil mist separation portion 120 facing the rotating bearing 300. Specifically, by having multiple axial abutment portions simultaneously abut against the rotating bearing 300 axially, reliable axial positioning of the rotating bearing 300 is ensured. Optionally, the axial abutment portions are arranged in a claw shape.

[0034] like Figure 2 As shown, in this embodiment, the rotating bearing 300 includes an outer bearing ring, an inner bearing ring, and a bearing cage 310 disposed between the outer and inner bearing rings. A first opening 320 communicating with the second cavity 210 is provided between the bearing cage 310 and the outer bearing ring, and a second opening 330 communicating with the second cavity 210 is provided between the bearing cage 310 and the inner bearing ring. Specifically, the atomized lubricating oil in the second cavity 210 enters the rotating bearing 300 through the first opening 320 and the second opening 330 to lubricate the rotating bearing 300 and extend the normal operating time of the rotating bearing 300 after the atomized lubricating oil supply is interrupted.

[0035] like Figure 1 As shown, in this embodiment, the second cavity 210 is provided with an oil return pool and an oil nozzle 220 for spraying lubricating oil onto the rotating bearing 300, and the first cavity 600 is provided with an oil return hole communicating with the oil return pool. Specifically, when the aircraft engine is operating normally, lubricating oil is sprayed onto the rotating bearing 300 through the oil nozzle 220 to lubricate the rotating bearing 300. The lubricating oil in the second cavity 210 is collected through the oil return pool, and the lubricating oil in the first cavity 600 is collected through the oil return hole. After the oil nozzle 220 stops spraying lubricating oil, the lubricating oil in the second cavity 210 is atomized, so that the atomized lubricating oil can lubricate the rotating bearing 300.

[0036] The aero-engine of this embodiment includes the aforementioned bearing cavity sealing and bleed air structure. Specifically, by adopting the aforementioned bearing cavity sealing and bleed air structure in the aero-engine, the design and assembly difficulty of the bearing housing 200 and related structures in the aero-engine can be reduced while meeting the requirements of the lubricating oil interruption test. It is highly practical and suitable for widespread promotion and application.

[0037] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A bearing cavity sealing and air-guiding structure, characterized in that, The device includes a sealing ring housing (100), a bearing housing (200) disposed within the sealing ring housing (100), a rotating bearing (300) disposed within the bearing housing (200), a rotor assembly (400) disposed within the sealing ring housing (100), and a sealing grate ring (500) sleeved outside the rotor assembly (400). The sealing ring housing (100) and the bearing housing (200) together form a first cavity (600). The sealing ring housing (100) and the sealing grate ring (500) together form an axially oriented inlet for introducing sealing gas, which is positioned opposite to the rotating bearing (300). An air inlet channel (800) is provided between the air passage (700), the sealing ring housing (100), and the rotating bearing (300), respectively communicating with the first cavity (600) and the induced air passage (700). The bearing housing (200) includes a second cavity (210) communicating with the inner cavity of the rotating bearing (300) for containing atomized lubricating oil and a return channel (900) communicating with the first cavity (600) and the second cavity (210) respectively. The end of the induced air passage (700) near the rotating bearing (300) is provided with a guide assembly for guiding the sealing gas to the induced air passage (800). The sealing ring housing (100) includes a grate sealing part (110) that abuts against the sealing grate ring (500) to prevent lubricating oil from leaking from the air intake channel (700) and an oil mist separation part (120) that surrounds the rotating bearing (300) to form an air intake channel (800). The grate sealing part (110) and the oil mist separation part (120) surround the sealing grate ring (500) to form an air intake channel (700). The oil mist separation part (120) has oil mist separation holes (130) that are respectively connected to the air intake channel (700) and the first cavity (600) in the radial direction.

2. The bearing cavity sealing and air ducting structure according to claim 1, characterized in that, Multiple oil mist separation holes (130) are provided, and the multiple oil mist separation holes (130) are arranged at intervals along the axial and / or circumferential directions on the oil mist separation section (120).

3. The bearing cavity sealing and air ducting structure according to claim 1, characterized in that, The flow guiding assembly includes a first flow guiding boss (121) formed by the oil mist separation section (120) extending radially toward the sealing grate ring (500) and a second flow guiding boss (510) formed by the sealing grate ring (500) extending radially toward the oil mist separation section (120). The axial distance between the first flow guiding boss (121) and the rotating bearing (300) is greater than the axial distance between the second flow guiding boss (510) and the rotating bearing (300).

4. The bearing cavity sealing and air ducting structure according to claim 1, characterized in that, The end face of the grate sealing part (110) facing the sealing grate ring (500) is provided with a polishing layer, and the end face of the sealing grate ring (500) facing the grate sealing part (110) is provided with sealing grates that abut against the polishing layer.

5. The bearing cavity sealing and air ducting structure according to claim 1, characterized in that, The oil mist separator (120) has an axial abutment portion on its axial end facing the rotating bearing (300) for axially abutting the rotating bearing (300) to axially position the rotating bearing (300).

6. The bearing cavity sealing and air ducting structure according to claim 5, characterized in that, Multiple axial abutment portions are provided, and the multiple axial abutment portions are arranged circumferentially at intervals on the axial end of the oil mist separation portion (120) facing the rotating bearing (300).

7. The bearing cavity sealing and venting structure according to any one of claims 1-6, characterized in that, The rotating bearing (300) includes an outer bearing ring, an inner bearing ring, and a bearing cage (310) disposed between the outer bearing ring and the inner bearing ring. A first opening (320) communicating with a second cavity (210) is provided between the bearing cage (310) and the outer bearing ring. A second opening (330) communicating with the second cavity (210) is provided between the bearing cage (310) and the inner bearing ring.

8. The bearing cavity sealing and venting structure according to any one of claims 1-6, characterized in that, The second cavity (210) is provided with an oil return pool and an oil nozzle (220) for spraying lubricating oil into the rotating bearing (300). The first cavity (600) is provided with an oil return hole that communicates with the oil return pool.

9. An aircraft engine, characterized in that, Includes the bearing cavity sealing and air ducting structure as described in any one of claims 1-8.

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