CN-116291874-B - Method and system for extracting front-end power of large bypass ratio aero-engine

CN116291874BCN 116291874 BCN116291874 BCN 116291874BCN-116291874-B

Abstract

The invention provides a method and a system for extracting front power of an aeroengine with a large bypass ratio, wherein the system comprises a low-voltage rotor front power extraction subsystem, the low-voltage rotor front power extraction subsystem comprises a supporting structure, the supporting structure comprises an outer casing and an inner casing which are coaxial, the outer casing is connected with a fan casing, the front end of the inner casing is connected with the outer casing through a bearing support plate, the rear end of the inner casing is in lap joint with a low-voltage rotor disc, and an inner cavity at the front end of the inner casing is provided with a generator. The method comprises a front power extraction mode design step and a front power extraction system design step, wherein the front power extraction mode design step comprises the steps of front power extraction and distribution of a high-voltage rotor and a low-voltage rotor. The method and the system designed by the invention extract the low-voltage rotor power in a preposed power extraction mode, ensure the power consumption requirement of the aeroengine under the condition of ensuring the margin of the air compressor, make up the blank of the industry and have important guiding significance.

Inventors

ZHAO DAN
FU YU
XIANG YING
DONG HANBIN
XU LIANGLIANG
SHAO JIANBO
HUANG FA

Assignees

中国航发四川燃气涡轮研究院

Dates

Publication Date: 20260505
Application Date: 20230224

Claims (3)

1. The high bypass ratio aeroengine front-end power extraction system is characterized by comprising a low-pressure rotor front-end power extraction subsystem, wherein the low-pressure rotor front-end power extraction subsystem comprises a support structure and a front-end power transmission device; The supporting structure comprises an outer casing (2) and an inner casing (4) which are coaxial, the outer casing (2) is connected with a fan casing (1), the front end of the inner casing (4) is connected with the outer casing (2) through a bearing support plate (8), the rear end of the inner casing (4) is lapped with a low-voltage rotor blade disc, a generator (11) is assembled in an inner cavity at the front end of the inner casing (4), the generator (11) is a permanent magnet motor or a three-stage motor, the bearing support plate (8) is of a hollow structure and is used for arranging a power transmission cable and a motor control cable, and the axial distance between the bearing support plate (8) and the fan rotor blade (3) is 1-2 times the chord length of the fan rotor blade (3); the front power transmission device is located in the inner cavity of the rear end of the inner casing (4), is arranged between the low-voltage rotor and the generator and comprises a driving shaft (5) and a power output shaft (7) which are sequentially connected, one end of the driving shaft (5) is arranged on the low-voltage rotor disc, the other end of the driving shaft is connected with the power output shaft (7), the other end of the power output shaft (7) is connected with the generator, and a membrane disc coupler (6) is arranged between the driving shaft (5) and the power output shaft (7).
2. The high bypass ratio aircraft engine front power extraction system of claim 1, wherein the low-pressure rotor front power extraction subsystem further comprises a cooling structure, the cooling structure comprises a cooling exhaust pipe (9) and a cooling air supply pipe (14) which are positioned in an inner cavity of the bearing support plate (8), and through holes through which the cooling exhaust pipe (9) and the cooling air supply pipe (14) penetrate are formed in the outer casing (2) and the inner casing (4).
3. The high bypass ratio aircraft engine forward power extraction system of claim 1 wherein the low pressure rotor forward power extraction subsystem further comprises an intake cap (12), the intake cap (12) being disposed at the support structure forward end; and a heating element (10) is arranged on the air inlet cap cover (12) and/or the bearing support plate (8).

Description

Method and system for extracting front-end power of large bypass ratio aero-engine Technical Field The invention belongs to the field of aeroengines, relates to an engine power extraction design technology, and particularly relates to a method and a system for extracting front-end power of an aeroengine with a large bypass ratio. Background With the development of communication technology, computer technology and on-board laser weapons, aircraft demand for electrical power has increased, such that aircraft engines are facing increasingly greater power extraction (i.e., the generation of electrical energy by engine-driven generators, the portion of the energy consumed by the engine being referred to as power extraction) demands. For example, when an aircraft performs a flight mission at high altitude, when work generated by a turbine is reduced, the power extraction capability of an engine is reduced, and if high power extraction is continued, the surge margin of the engine is insufficient to influence the flight safety, and if the flight safety is ensured, the high power extraction requirement of the aircraft cannot be met. For another example, modern aero-engines mainly adopt a double-rotor structure, engine power extraction mainly comes from a high-pressure rotor, wherein when a medium and small thrust engine works in a high-altitude state, the margin of a compressor is obviously reduced when enough power is extracted from the high-pressure rotor due to small power emitted by a turbine. Meanwhile, a front-mounted low-voltage power extraction method for the aero-engine with the large bypass ratio is not designed at present. Disclosure of Invention The invention aims to disclose a method and a system for extracting front-mounted power of an aeroengine with a large bypass ratio, which can meet the power requirement of an aircraft on the premise that the flight safety cannot be ensured, and can also solve the problems of installation and working reliability of a power extraction system. The technical scheme for realizing the aim of the invention is as follows: in a first aspect, the present invention provides a high bypass ratio aircraft engine forward power extraction system comprising a low pressure rotor forward power extraction subsystem comprising a support structure, a forward power transfer device. The support structure comprises an outer casing and an inner casing which are coaxial, the outer casing is connected with the fan casing, the front end of the inner casing is connected with the outer casing through a bearing support plate, the rear end of the inner casing is in lap joint with the low-pressure rotor disc, and a generator is assembled in an inner cavity of the front end of the inner casing. Because the low-voltage rotor has lower rotating speed and low extractable power, the generator is heavier and larger in size, and therefore, in order to ensure the reliable installation and force transmission of the generator, the generator is installed at the bearing support plate, and the axial distance between the bearing support plate and the fan rotor blade is longer, so that the length of the power transmission device between the motor and the low-voltage rotor is longer. Further, the axial distance between the bearing support plate and the fan rotor blade is 1-2 times the chord length of the fan rotor blade, so that the aerodynamic stability of the fan rotor is ensured. Further, the front power transmission device is located in the inner cavity of the rear end of the inner casing, one end of the front power transmission device is connected with the generator, and the other end of the front power transmission device is connected with the low-voltage rotor blade disc. Still further, leading power transmission device is located between low pressure rotor and the generator, solves the installation and the transmission stability that transmission device length is longer arouses simultaneously, designs leading power transmission system, and leading power transmission system includes the drive shaft that connects gradually, the drive shaft other end sets up on low pressure rotor leaf dish, the other end with power output shaft connection, just the other end of power output shaft with the generator is connected. Preferably, a membrane disc coupler is arranged between the driving shaft and the power output shaft. Further, the low-pressure rotor preposed power extraction subsystem further comprises a cooling structure, the cooling structure comprises a cooling exhaust pipe and a cooling air supply pipe which are positioned in the inner cavity of the bearing support plate, and through holes through which the cooling exhaust pipe and the cooling air supply pipe penetrate are formed in the outer casing and the inner casing. Further, the low pressure rotor front power extraction subsystem further comprises an air intake cap disposed at the front end of the support structure; The air inlet cap cover and/or the bea