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High-power gas turbine engine

A gas turbine and engine technology, applied to gas turbine devices, engine components, machines/engines, etc., can solve the problems of insufficient oil supply pressure in the lubricating oil system, increase the rotational resistance of the main shaft, adjust the oil supply pressure, etc., to avoid lubricating oil The effect of low pressure, reduced wear rate, and reduced rotational resistance

Active Publication Date: 2021-01-15
上海尚实航空发动机股份有限公司
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

During high-speed operation, the engine needs to continuously supply lubricating oil to the bearing cavity to ensure the normal operation of the bearing. In order to prevent the leakage of lubricating oil, a sealing device needs to be installed at the end of the bearing cavity. The existing technology generally uses a sliding sealing ring for sealing. Strict, there is relative friction between the sealing ring and the main shaft, which increases the rotational resistance of the main shaft on the one hand, and on the other hand, the high-speed rotation of the main shaft makes the sealing ring wear faster and the service life is low
The existing technology also proposes a wind pressure sealing mechanism, which introduces the high-pressure airflow in the high-pressure air duct into the gap between the bearing cavity and the main shaft to form a high-pressure air gap, so as to achieve the purpose of sealing. This sealing method When the engine is running normally, it can achieve a good sealing effect, but when the engine is started or stopped, the wind pressure in the high-pressure air duct may be lower than the wind pressure required for sealing, and the lubricating oil may still flow from the The air gap seeps out; in addition, the air pressure in the bearing cavity will fluctuate, and the existing lubricating oil supply system cannot adjust the oil supply pressure according to the air pressure fluctuation in the bearing cavity, so when the pressure in the bearing cavity rises, it may cause the lubricating oil system to Insufficient oil supply pressure

Method used

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Embodiment Construction

[0025] In order to make the objects and advantages of the present invention clearer, the present invention will be specifically described below in conjunction with examples. It should be understood that the following words are only used to describe one or several specific implementation modes of the present invention, and do not strictly limit the protection scope of the specific claims of the present invention.

[0026] Such as figure 1 , 4 As shown, a high-power gas turbine engine includes a casing, and a bearing bracket 20 is fixedly arranged in the casing. The main shaft 10 is rotatably connected with the bearing bracket 20 through a bearing 60. The front end of the main shaft 10 is connected with a compressor impeller, and the rear end of the main shaft 10 is Connect the turbine, the bearing bracket 20 is located in the high-pressure air duct 1 between the compressor and the turbine; there is an annular clamp cavity 21 between the main shaft 10 and the bearing bracket 20...

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Abstract

The invention belongs to the technical field of aero-engine manufacturing, and particularly relates to a high-power gas turbine engine. The high-power gas turbine engine comprises a casing; a bearingsupport is arranged in the casing; a spindle is rotatably connected with the bearing support through a bearing; the front end of the spindle is connected with a compressor impeller; the rear end of the spindle is connected with a turbine; the bearing support is located in a high-pressure air duct; an annular clamping cavity is formed between the spindle and the bearing support; an oil inlet hole and an oil outlet hole are formed in the bearing support; an end cover is arranged at the end of the bearing support; a sealing mechanism is arranged between the inner ring surface of the end cover andthe spindle; and the sealing mechanism comprises an annular air gap formed between the inner ring surface of the end cover and the outer ring surface of the spindle at intervals and a movable sealingring arranged on the through-flow section of the annular air gap. Sliding oil is prevented from seeping from the annular air gap under the condition of low rotating speed, the abrasion speed of the sealing ring under the condition of high rotating speed is effectively reduced, the service life of the sealing ring is prolonged, meanwhile the rotating resistance of the spindle is reduced, too low pressure of lubricating oil is avoided, and reliable operation of the bearing is guaranteed.

Description

technical field [0001] The invention belongs to the technical field of aero-engine manufacturing, and in particular relates to a high-power gas turbine engine. Background technique [0002] The aero-engine is mainly composed of a main shaft, a compressor, a turbine, a casing, a fuel system, and a lubricating oil system. A high-pressure air passage is formed between the engine and the turbine, and the nozzle and ignition mechanism of the fuel system are generally located in this air passage, and the bearing support mechanism of the main shaft is also generally installed in this position. During high-speed operation, the engine needs to continuously supply lubricating oil to the bearing cavity to ensure the normal operation of the bearing. In order to prevent the leakage of lubricating oil, a sealing device needs to be installed at the end of the bearing cavity. The existing technology generally uses a sliding sealing ring for sealing. Strictly, there is relative friction bet...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/00F02C7/06F01D11/04
CPCF01D11/04F02C7/00F02C7/06
Inventor 刘国峰周翔郭义黄啸
Owner 上海尚实航空发动机股份有限公司