CN-122016328-A - Remote sensing signal transmission system for motive stress of aero-engine

CN122016328ACN 122016328 ACN122016328 ACN 122016328ACN-122016328-A

Abstract

The invention discloses an aeroengine mechanical stress telemetering signal transmission system which comprises a signal acquisition module, a signal receiving module and a power supply module which are respectively and independently arranged in an engine, wherein the signal acquisition module and the signal receiving module are used for carrying out signal transmission through an antenna, the signal acquisition module comprises an amplifier and a DC/AC conversion module, the signal receiving module comprises a signal receiver and an upper computer, the non-contact signal transmission and power supply design is adopted, the traditional slip ring is thoroughly abandoned from being connected with a wire, the problem of abrasion under high rotating speed is solved, and a telemetering measuring device can be modularized and miniaturized and is arranged in the engine, so that the purpose of measuring the dynamic stress of a compressor rotor and a turbine rotor is achieved.

Inventors

GUO TIANSHUI
HUANG FANG
QIN ZHIQIAN
XU JIE
LI DONG
XU JUN
Zhou kunlun

Assignees

中国航发贵阳发动机设计研究所

Dates

Publication Date: 20260512
Application Date: 20260112

Claims (10)

1. The remote sensing signal transmission system for the mechanical stress of the aeroengine is characterized by comprising a signal acquisition module, a signal receiving module and a power supply module which are respectively and independently arranged in the engine, wherein the signal acquisition module and the signal receiving module are used for transmitting signals through an antenna, the signal acquisition module comprises an amplifier and a DC/AC conversion module, and the signal receiving module comprises a signal receiver and an upper computer; The amplifier receives and amplifies dynamic stress signals of an engine compressor and a turbine rotor, codes and modulates the dynamic stress signals into radio frequency signals through a DC/AC conversion module, and then transmits the radio frequency signals to the signal receiver through an antenna; the power supply module adopts a loose coupling induction power supply mode, and a power supply at the end of the signal receiving module is transmitted to the signal acquisition module through an induction power supply exciter.
2. The system of claim 1, wherein the antenna comprises a transmitting antenna and a receiving antenna, the transmitting antenna is connected with the DC/AC module through a capacitor and an inductor which are connected in parallel, and the receiving antenna is connected with the signal receiver.
3. The system of claim 2, wherein the transmitting antenna is fixed to an outer wall of a ring of a labyrinth of the engine, and the receiving antenna is mounted to the stator of the engine by a receiving mount and is opposite to the transmitting antenna.
4. The system for transmitting the mechanical stress telemetry signal of the aeroengine according to claim 3, wherein the receiving mounting seat is fixed on the engine stator through bolts, the outer wall of the receiving mounting seat is attached to the engine stator, supporting rings coaxial with the rotating shaft of the engine are arranged at the inner end and the outer end of the receiving mounting seat, and the receiving antenna is fixed on the supporting rings at the inner side through bolts.
5. The system of claim 2, wherein the transmitting antenna is less than 1/4 wavelength long and the receiving antenna is a loop antenna.
6. The system of claim 1, wherein the power supply module comprises a primary coil and a secondary coil, the primary coil is connected to an output end of an inductive power supply exciter, an input end of the inductive power supply exciter is connected to a signal receiver to draw power, and the secondary coil is respectively powered by the amplifier and the DC/AC conversion module.
7. The system of claim 6 wherein capacitors are connected in parallel between the primary and secondary windings.
8. The system of claim 7, wherein the primary and secondary windings are wound with copper wire having a diameter of 0.3 mm.
9. The system of claim 8, wherein the primary coil is mounted on an outer ring of the receiving mount, the secondary coil is mounted between the engine zero-order disk and the stator via a secondary coil mount, the amplifier and DC/AC conversion module are mounted between the engine zero-order disk and the primary disk via a module mount, the secondary coil mount is coaxially mounted on the zero-order disk, a secondary support ring concentric with the primary coil is provided at an edge thereof, and the secondary coil is fixed on the secondary support ring.
10. The system of claim 9, wherein the plurality of module mounts are uniformly arranged in the circumferential direction of the zero-order disc according to the number of the signal acquisition modules, and each module mount is provided with two through holes matched with the shapes of the amplifier and the DC/AC conversion module respectively.

Description

Remote sensing signal transmission system for motive stress of aero-engine Technical Field The invention relates to an aeroengine motor stress telemetry signal transmission system. Background Aircraft engines are hearts of aircraft, and performance of the aircraft directly influences performance and fight performance of the aircraft. During the running process of the engine, the dynamic stress parameter measurement of the rotor is a very important test content of the engine test, and is also an important technical index for measuring the structural strength and the working reliability of the engine. However, for high-speed rotating parts, obtaining accurate dynamic stress parameters under severe working conditions such as a small space, a high rotating speed, a high temperature and the like has been a difficult problem. Currently, the dynamic stress measurement of rotor components generally employs wireless telemetry. The wireless telemetry technology has the advantages of flexible installation, multiple channels, wide application range and the like, but when the wireless telemetry technology is applied to the measurement of the mechanical stress of the aero-engine, telemetry equipment cannot be installed in the engine due to the large volume and can only be installed at the places with large space such as the fairing, the shaft end and the like, so that the dynamic stress of the fan rotor component can be measured only in the whole machine measurement, and the dynamic stress of the rear end rotor component of the engine such as the air compressor, the turbine and the like cannot be measured. Disclosure of Invention The invention aims at solving the problem that the existing telemetry system cannot measure and acquire dynamic stress data of a compressor and a turbine rotor, and designs a modularized and miniaturized dynamic stress measuring device of the telemetry device, which is decomposed into modules such as a telemetry transmitting antenna, a telemetry receiving antenna, a power supply coil, an amplifier module, an AC/DC conversion module, a cable and the like according to the composition of the telemetry device, and corresponding mounting seat structures are designed and mounted according to the internal structure of an engine and are mounted in a space between a zero rotor and a first-stage rotor of the compressor. The technical scheme of the invention is as follows: The system comprises a signal acquisition module, a signal receiving module and a power supply module which are respectively and independently installed in an engine, wherein signal transmission is carried out between the signal acquisition module and the signal receiving module through an antenna, the signal acquisition module comprises an amplifier and a DC/AC conversion module, and the signal receiving module comprises a signal receiver and an upper computer; The amplifier receives and amplifies dynamic stress signals of an engine compressor and a turbine rotor, codes and modulates the dynamic stress signals into radio frequency signals through a DC/AC conversion module, and then transmits the radio frequency signals to the signal receiver through an antenna; the power supply module adopts a loose coupling induction power supply mode, and a power supply at the end of the signal receiving module is transmitted to the signal acquisition module through an induction power supply exciter. The antenna comprises a transmitting antenna and a receiving antenna, wherein the transmitting antenna is connected with the DC/AC module through a capacitor and an inductor which are connected in parallel, and the receiving antenna is connected with the signal receiver. The transmitting antenna is fixed on the outer wall of the comb ring of the engine, and the receiving antenna is arranged on the engine stator through the receiving installation seat and is opposite to the transmitting antenna. The receiving installation seat is fixed on the engine stator through bolts, the outer wall of the receiving installation seat is attached to the engine stator, supporting rings coaxial with the rotating shaft of the engine are arranged at the inner end and the outer end of the receiving installation seat, and the receiving antenna is fixed on the supporting rings at the inner side through bolts. The length of the transmitting antenna is smaller than 1/4 wavelength, and the receiving antenna is a loop antenna. The power supply module comprises a primary coil and a secondary coil, the primary coil is connected to the output end of the induction power supply exciter, the input end of the induction power supply exciter leads out power from the signal receiver, and the secondary coil is respectively powered with the amplifier and the DC/AC conversion module. And capacitors are connected in parallel between the two poles of the primary coil and the secondary coil. The primary coil and the secondary coil are wound by copper wires with the diameter of 0.3 mm. The primary