Gas turbine engine and oil drainage method of gas turbine engine
A technology of gas turbine and engine, which is applied in the field of gas turbine engine and gas turbine engine oil discharge, which can solve the problems such as difficult to remove, candle flames at the tail of the engine, and limited lubricating oil, so as to achieve the effect of simple and convenient cleaning
Active Publication Date: 2022-03-29
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology
Since the deposited lubricating oil is located in the low-pressure turbine casing, there are components such as the tail nozzle assembly behind the low-pressure turbine casing, and the lubricating oil deposited in the low-pressure turbine casing is limited by the concave-convex configuration of the structural flow channel and is difficult to remove
After the deposited lubricating oil reaches a certain amount, it may cause tail candles during subsequent engine operation, posing a safety risk
Method used
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[0025] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0026] The relative arrangements of components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. At the same time, it should be understood that, for the convenience of descriptio...
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The invention discloses a gas turbine engine and an oil drainage method of the gas turbine engine. The gas turbine engine comprises a low-pressure turbine casing, a low-pressure turbine casing and an oil drainage device, an exhaust nozzle; and the communicating pipe is communicated with the low-pressure turbine casing and the exhaust nozzle, is used for guiding the deposited lubricating oil in the low-pressure turbine casing into the exhaust nozzle, and comprises an inlet end connected with the low-pressure turbine casing and an outlet end connected with the exhaust nozzle. The gas turbine engine of the present invention facilitates the removal of leaked lubricating oil deposited in the low pressure turbine casing.
Description
technical field [0001] The invention relates to the technical field of aeroengines, in particular to a gas turbine engine and an oil discharge method for the gas turbine engine. Background technique [0002] A gas turbine engine includes components such as a compressor, a combustion chamber, a turbine, and an exhaust nozzle. Gas turbine engines also include bearings for mounting the turbine rotor and an oil system for lubricating and cooling the bearings. A sealing device is arranged in the engine to prevent the lubricating oil of the lubricating oil system from leaking. For example, during the normal operation of the engine, the boosted air pressure of the engine is greater than the oil supply pressure, and the lubricating oil is sealed in the bearing cavity by the high-pressure boosted air to prevent the lubricating oil from leaking out. [0003] However, there are still some oil leakage conditions in the engine. For example, under engine starting, cold running, parking...
Claims
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IPC IPC(8): F02C7/06F01D25/12
CPCF02C7/06F01D25/125
Inventor 朱文毅陶金谷裕
Owner AECC COMML AIRCRAFT ENGINE CO LTD