Close-distance telemetering transmission device for rotating part of aero-engine

Abstract

The invention provides an aero-engine rotating part short-distance telemetering transmission device, and the device comprises a switching section which is connected with an aero-engine rotating shaft and is used for leading out a sensor signal disposed on an aero-engine rotor to the switching section, and the switching section comprises a switching structure, a switching module, and an annular module; wherein the switching structure is connected with the switching module, and the switching module is connected with the annular module; the telemetering transmitting device is connected with the switching section and used for transmitting the sensor signals acquired by the switching section through wireless signals, and the telemetering transmitting device comprises a telemetering transmitting device structure and a main module; the telemetering receiving device is connected with the engine stator and used for receiving the wireless signals transmitted by the telemetering transmitting device; wherein the switching section, the telemetering transmitting device and the telemetering receiving device are all of a revolving body structure.

Description

Technical Field

[0001] The present invention relates to the technical field of aero - engines, and particularly to a close - range telemetry transmission device for rotating components of an aero - engine. Background Art

[0002] In the aviation industry, from the research and development of aircraft and engines to mass production, scientific research flight tests and commissioning for certification are essential. Compared with the airborne equipment on the aircraft, the engine is always in a high - speed rotating state, and it is very easy to fail during continuous operation, which will not only damage the equipment but also affect the production efficiency of the aviation industry, bringing economic losses to the aviation industry and even serious consequences such as casualties. Therefore, in order to improve the safety and reliability of rotating machinery, it is of great significance to study the transmission of dynamic parameters of rotating components.

[0003] Due to the differences in the structures of the whole aero - engines and their components of different models, the number of measurement points of the measured fan, compressor, and turbine also varies. Currently, the mainstream telemetry devices are all designed in a customized manner according to the installation position characteristics of the engine. Such designed telemetry devices have high verification costs and long cycles, and cannot meet the rapid test requirements of today's aero - engine rotating parts. To solve the compatibility problem of the telemetry transmission device, it is necessary to design a close - range telemetry transmission device including an adapter section and a telemetry transmitter. It has the characteristics of small size, light weight, and strong compatibility. For different models of engines, only by quickly adapting the design of the adapter section according to the characteristics of the engine shaft, it can be directly assembled to the engine for testing the parameters of high - speed rotating parts. Summary of the Invention

[0004] In view of this, the present invention provides a close - range telemetry transmission device for rotating components of an aero - engine, so as to achieve the purpose of directly assembling the engine for testing the parameters of high - speed rotating parts by quickly adapting the design of the adapter section.

[0005] The present invention provides the following technical solutions: A close - range telemetry transmission device for rotating components of an aero - engine, comprising: an adapter section, connected to the aero - engine shaft, for leading out the sensor signals arranged on the aero - engine rotor to the adapter section. The adapter section includes an adapter structure, an adapter module, and an annular module; wherein, the adapter structure is connected to the adapter module, and the adapter module is connected to the annular module; a telemetry transmitter, connected to the adapter section, for wirelessly transmitting the sensor signals obtained by the adapter section. The telemetry transmitter includes a telemetry transmitter structure and a main module; a telemetry receiver, connected to the engine stator, for receiving the wireless signals transmitted by the telemetry transmitter; wherein, the adapter section, the telemetry transmitter, and the telemetry receiver are all of a rotary body structure.

[0006] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the present invention at least include: The telemetry transmission device of the present invention has a small volume, multiple composite measurement points, and is widely compatible with the telemetry test scenarios of the whole aeroengine and the shaft ends of parts and components of different models. It can meet the dynamic stress and temperature field test scenarios with a rotational speed not exceeding 20,000 rpm, a working temperature range not exceeding 85°C, no more than 20 temperature measurement points, no more than 20 strain measurement points, and a rotor-stator clearance not exceeding 10 mm. The successful application of this telemetry transmission device solves the compatibility problem of telemetry transmission devices for the whole engines and parts and components of different models, saves a large amount of research and development costs, and effectively shortens the research and development cycle of aeroengines. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0008] Figure 1 is the installation schematic diagram of the embodiment of the present invention on an aeroengine;

[0009] Figure 2 is the schematic diagram of the adapter section of the embodiment of the present invention;

[0010] Figure 3 is the schematic diagram of the main module of the embodiment of the present invention;

[0011] Figure 4 is the schematic diagram of the telemetry transmitting device of the embodiment of the present invention;

[0012] Figure 5 is the schematic diagram of the counterbore structure of the embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0013] The embodiments of the present application will be described in detail below with reference to the drawings.

[0014] The following specific examples illustrate the implementation manners of the present application. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of them. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts belong to the scope of protection of the present application.

[0015] As shown Figures 1 to 5 in the figure, the present invention provides a close-range telemetry transmission device for a rotating component of an aeroengine, which is composed of an adapter section (SW), a telemetry transmitting device (TD) and a telemetry receiving device (RD). The specific installation steps are as follows:

[0016] The adapter section (SW) is bolted to the aeroengine rotating shaft through circumferentially evenly distributed adapter section mounting holes (D), and the mounting flange at the other end of the adapter section (SW) is fixed to the telemetry transmitting device (TD) through the telemetry transmitting device mounting holes (P).

[0017] The main module (MM) of the telemetry transmitting device (TD) is inserted into the annular module jack (J) of the adapter section (SW) through the main module pins (K) to achieve electrical signal connection.

[0018] The telemetry receiving device (RD) is fixed to the engine stator through circumferentially evenly distributed telemetry receiving device structure mounting holes (X), ensuring that the distance between its receiving antenna and the transmitting antenna of the telemetry transmitting device (TD) is ≤10 mm to meet the rotating-stator distance limit.

[0019] The adapter section (SW) is composed of the following components:

[0020] Adapter structure (A): Adopting a rotating body structure, with 8 adapter section mounting holes (D) arranged circumferentially, the hole diameter is Φ5 mm, and it is bolted to the engine rotating shaft; there are internal adapter module mounting holes (E) (Φ3 mm) and mounting grooves (F) for fixing the adapter module (B), and the depth of the mounting groove (F) is 4 mm; the position of the mounting holes on the mounting flange of the adapter section completely matches the mounting holes of the telemetry transmitting device (TD), with a tolerance of ±0.1 mm.

[0021] Adapter module (B): Embedded in the mounting groove (F) and fixed through the adapter module mounting holes (E) (Φ3 mm); there are internal sensor lead holes (G) (Φ1.5 mm) for leading out the temperature, strain or pressure sensor leads inside the rotating shaft; sensor lead solder joints (H) are arranged on the surface, using silver-copper alloy solder, and the solder joint spacing is 2 mm; the adapter module jack (I) has an asymmetric layout (offset angle 15°) to prevent misinsertion.

[0022] Annular module (C): A ring structure, with an outer diameter of Φ60 mm, an inner diameter of Φ50 mm, and a thickness of 3 mm; an annular module jack (J) (Φ2 mm) is arranged inside, with the same position and size as the adapter module jack (I);

[0023] During installation, avoid the sensor lead solder joints (H) and adapter module mounting holes (E) of the adapter module (B) to ensure no mechanical interference.

[0024] Telemetry transmitter structure (TS): Rotating body structure, axially arranged telemetry transmitter mounting hole (P) (Φ5mm), connected to the adapter section (SW); internally provided with: telemetry module mounting slot (Q) (size 30mm×20mm×5mm), used to install the telemetry module; power module mounting slot (R) (size 25mm×15mm×6mm), built-in lithium battery (3.7V, 2000mAh); RF antenna and inductive power receiving module lead slot (S) (width 1.2mm), used to lay the RF antenna lead; transmitting antenna and inductive power receiving module mounting slot (T) (Φ8mm), fixed the transmitting antenna.

[0025] Main module (MM): thickness is 2.5mm (meeting the requirement of ≮2mm), made of aluminum alloy; the main module pin (K) (Φ1.8mm) is plugged into the ring module jack (J), and the pin length is 5mm; the power module interface (L) is a countersunk structure, with a top hole depth of 1mm and a bottom hole depth of 1.5mm (main module thickness 2.5mm - top hole depth 1mm = 1.5mm), a bottom hole diameter of Φ0.95mm, and a top hole diameter of Φ1.25mm; the telemetry module interface (N) and the RF antenna interface (O) use the same countersunk structure to ensure signal shielding; the main module mounting hole (M) (Φ2.5mm) is fixed to the telemetry transmitter structure (TS) by screws.

[0026] The structural parameters of the telemetry receiving device (RD) are as follows:

[0027] The rotating structure has an outer diameter of Φ55mm and an inner diameter of Φ45mm; six telemetry receiving device structure mounting holes (X) (Φ4mm) are arranged circumferentially and fixed to the engine stator by bolts; the internal mounting slot (Y) (size 25mm×15mm×5mm) has a built-in receiving antenna (frequency 2.4GHz, gain 5dBi) aligned with the transmitting antenna; the inductively powered transmitting module (output power 10W) powers the telemetry transmitting device (TD) through electromagnetic induction; the signal processing unit is integrated at the bottom of the mounting slot (Y), using an FPGA chip to analyze the wireless signal and output it to the monitoring terminal.

[0028] Workflow:

[0029] The temperature, strain or pressure sensor signals on the rotor are led out through the sensor lead hole (G) of the adapter module (B), welded at the welding point (H) and then transmitted to the ring module (C);

[0030] The main module (MM) receives the signal through the pin (K), the telemetry module modulates the signal (sampling rate 1kHz), and transmits it through the RF antenna (2.4GHz frequency band);

[0031] The receiving antenna of the telemetry receiving device (RD) captures the signal, which is transmitted to the ground monitoring system after being decoded by the FPGA.

[0032] Parameter limitations: Maximum rotational speed: ≤ 20,000 rpm; Operating temperature range: -40°C to +85°C (meeting the limitation of ≯ 85°C); Number of measuring points: Temperature measuring points ≤ 20, strain measuring points ≤ 20; Rotor-stator clearance: ≤ 10 mm; Signal transmission distance: ≤ 50 cm (short-distance telemetry).

[0033] The above is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in this application should be covered within the protection scope of this application. Therefore, the protection scope of this application shall be subject to the protection scope of the claims.

Claims

1. A close-range telemetry transmission device for an aero-engine rotating component, characterized in that, Including: A transition section (SW) that connects to the shaft of an aero-engine and is used to lead out the sensor signals arranged on the aero-engine rotor to the transition section (SW). The transition section (SW) includes a transition structure (A), a transition module (B), and an annular module (C); among them, the transition structure (A) is connected to the transition module (B), and the transition module (B) is connected to the annular module (C); A telemetry transmitting device (TD) that is connected to the transition section (SW) and is used to transmit the sensor signals obtained by the transition section (SW) through wireless signals. The telemetry transmitting device (TD) includes a telemetry transmitting device structure (TS) and a main module (MM); A telemetry receiving device (RD) that is connected to the engine stator and is used to receive the wireless signals transmitted by the telemetry transmitting device (TD); Among them, the transition section (SW), the telemetry transmitting device (TD), and the telemetry receiving device (RD) are all of rotary body structures.

2. The close-range telemetry transmission device for an aero-engine rotating component according to claim 1, characterized in that The transition structure (A) of the transition section (SW) is circumferentially provided with transition section mounting holes (D) for connecting to the shaft of the aero-engine; inside the transition structure (A), there are transition module mounting holes (E) and mounting grooves (F) for fixing the transition module (B); the transition module (B) includes sensor lead holes (G), sensor lead solder joints (H), transition module mounting holes (E), and transition module jacks (I); the annular module (C) is a circular ring structure, and inside it, there are annular module jacks (J) corresponding to the transition module jacks (I).

3. The close-range telemetry transmission device for an aero-engine rotating component according to claim 2, characterized in that The transition module jack (I) is designed with an asymmetric structure.

4. The close-range telemetry transmission device for an aero-engine rotating component according to claim 3, wherein, The telemetry transmitting device structure (TS) of the telemetry transmitting device (TD) is axially provided with telemetry transmitting device mounting holes (P), and inside it, there are a telemetry module mounting groove (Q), a power module mounting groove (R), a radio frequency antenna and an inductive power receiving module lead groove (S), and a transmitting antenna and an inductive power receiving module mounting groove (T); the main module (MM) includes main module pins (K), a power module interface (L), main module mounting holes (M), a telemetry module interface (N), and a radio frequency antenna and an inductive power receiving module interface (O), where the main module pins (K) are in the same position as the annular module jacks (J).

5. The close-range telemetry transmission device for an aero-engine rotating component according to claim 4, wherein, The power module interface (L), the telemetry module interface (N), and the radio frequency antenna and an inductive power receiving module interface (O) of the main module (MM) adopt counterbore structures.

6. The close-range telemetry transmission device for an aero-engine rotating component according to claim 5, characterized in that, The telemetry receiving device (RD) is circumferentially provided with telemetry receiving device structure mounting holes (X), and inside it, there are a receiving antenna and an inductive power transmitting module mounting groove (Y), and the position of the receiving antenna and an inductive power transmitting module mounting groove (Y) corresponds to the transmitting antenna and an inductive power receiving module mounting groove (T) of the telemetry transmitting device (TD).

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