Split type centrifugal ventilator structure of aero-engine
An aero-engine, split-type technology, applied in the direction of engine components, machine/engine, engine lubrication, etc., can solve the problems of high maintenance complexity, large number of engine parts, etc., and achieve good economy, low maintenance cost, and improved The effect of integrated design level
Active Publication Date: 2021-10-26
AECC HUNAN AVIATION POWERPLANT RES INST
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Problems solved by technology
[0005] The purpose of the present invention is to provide a split type centrifugal ventilator structure for an aero-engine, which solves the problem that in the prior art, the accessory drive gearbox needs to design a separate accessory installation space and power output port for the oil-gas separator, resulting in a large number of engine parts and complicated maintenance. high degree of problem
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[0027] In order to make the object, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be further described in detail through the following embodiments and in conjunction with the accompanying drawings. In the specification, the same or similar reference numerals designate the same or similar components. The following description of the embodiments of the present invention with reference to the accompanying drawings is intended to explain the general inventive concept of the present invention, but should not be construed as a limitation of the present invention.
[0028] In addition, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a comprehensive understanding of the embodiments of the present disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances,...
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The invention discloses a split type centrifugal ventilator structure of an aero-engine, and relates to the technical field of aero-engines, the split type centrifugal ventilator structure comprises a gear shaft, an oil-gas separator and a gear with a radial plate, wherein a gas channel is formed in one end of the gear shaft, and separated gas after oil-gas separation is discharged out of a gear box; the oil-gas separator is composed of an inner ring, an outer ring and a plurality of supporting walls between the inner ring and the outer ring, and the inner ring is provided with a plurality of first supporting parts and a plurality of second supporting parts; a plurality of inner ring claw grooves are formed in one end of the inner ring, and a plurality of outer ring claw grooves are formed in one end of the outer ring; the gear with the radial plate is used in cooperation with the oil-gas separator to prevent an oil-gas mixture from leaking from the oil-gas separator. Through the combined design of the gear and the oil-gas separator, gas-liquid separation can be effectively and stably carried out on oil and gas of the gear box while power is transmitted, large mounting space does not need to be occupied, the weight and the cost are reduced, and the integration design level of a gear box assembly is effectively improved.
Description
technical field [0001] The invention belongs to the technical field of aero-engines, in particular to an aero-engine split type centrifugal ventilator structure. Background technique [0002] The accessory transmission gearbox is a key component of an aero-engine. Its transmission gears will generate a lot of heat during operation, and it is necessary to continuously use lubricating oil for circulating heat dissipation and lubrication. During the lubricating oil circulation lubrication process, a large amount of heat will be generated inside the transmission gearbox. The gas-liquid mixture such as oil mist and oil gas will have a certain impact on the heat dissipation of the lubricating oil and the internal pressure of the gearbox. Therefore, it is necessary to use a corresponding device to separate the gas and liquid from the oil and gas in the gearbox; the traditional solution is in the attachment A separate installation interface platform is designed on the transmission g...
Claims
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Login to View More IPC IPC(8): F02C7/06F02C7/00
CPCF02C7/06F02C7/00Y02T50/40
Inventor 游志伟董红涛江平卢聪明薛成胡广存
Owner AECC HUNAN AVIATION POWERPLANT RES INST