JPH0756216B2 - Rotor rotation device for jet engine inspection - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a jet engine compressor and a rotor rotating device for inspecting turbine blades.

[0002]

2. Description of the Related Art Particularly in a jet engine used for an aircraft, even if the compressor and turbine blades are extremely small, they may cause a serious accident or a catastrophic disaster. Strictly inspected for damage. As an inspection method, an endoscope called a borescope is inserted into the engine through an inspection opening provided in each engine, and the state of the turbine blade is visually observed through this fiberscope or directly through a monitor screen. It is common to observe indirectly.

In the above inspection work, in order to move the turbine blade of the jet engine in accordance with the progress of work, the rotor is continuously or intermittently controlled by a pulse motor.

[0004]

However, with the increase in engine output and the increase in size, a high torque is required to rotate the rotor during inspection work. The pulse motor that generates the driving force becomes larger, and the mechanism that transmits the driving force of the pulse motor to the rotor becomes larger because it requires a large-scale reduction mechanism that uses spur gears to generate high torque. Tend to do. As described above, the inspection work efficiency is lowered due to the increase in the size and weight of the rotor rotating device.

[0005]

SUMMARY OF THE INVENTION In order to solve the above problems, an object of the present invention is to reduce the size and weight of a rotor rotating device that generates high torque. Therefore, a harmonic gear is used to transmit the rotational driving force of the pulse motor to the rotor. Although this harmonic gear is small and lightweight, it greatly reduces the rotation speed of the input pulse motor,
An extremely large torque can be generated even if the rotational driving force of the pulse motor is not so large.

[0006]

Embodiments of the present invention will be described below with reference to the accompanying drawings.

A rotor rotating device for inspecting a turbine blade of a jet engine according to the present embodiment includes a power feeding unit, a control unit,
And a drive unit. The following is a detailed explanation of each part.

[0008] feeding section in Figure 1 feed section, than the appropriate AC power source via the terminal 1 generates a pulse motor driving pulse output terminal 2 to input power. The terminal 3 is connected to the control unit and receives a control signal. The breaker 4 is an ON / OFF switch and is provided to protect the entire circuit from excessive voltage.

Control Unit FIG. 2 shows the control unit. The engine model display 5 is
The type of jet engine being inspected is lit up and displayed. The state selection display 6 displays the state of the compressor or turbine of the engine (for example, "HPT 1"). The turbine blade number display 7 is switched between clockwise rotation CW and counterclockwise rotation CCW,
Then, the count value is incremented from 1 and stopped when the total number of blades is reached. The CCW stops when the count value becomes 1 after subtracting the count value from the total number of blades. CW /
The CCW display 8 indicates that the number display 7 is CW.
Is displayed or CCW is displayed. The engine model selection switch 9 is switched according to the engine to be inspected. The reset switch 10 resets the blade number display. The interval switch 11 is
It is for selecting the time (several seconds) for stopping the rotating blade for inspection. The start / stop switch 12 is for starting or stopping the rotational drive of the rotor. The CW / CCW switch 13 is a switch for switching the rotation direction of the rotor. The blade position switch 14 is for setting the inspection position of the blade. The speed switch 15 changes the rotation speed of the rotor from 80 to 180 ° / Min. It is for adjusting within the range of. The foot switch jack 16 is a switch for connecting to a foot switch. The cable 17 is connected to the control unit.

Drive Unit FIG. 3 shows a drive unit 18 fixed to the jet engine to rotate the rotor. The drive unit 18 is fixed to the jet engine body via an adapter 19. Drive unit 18
Is equipped with a chopper style constant current drive 5-phase step pulse motor 20. The motor 20 is rotated by inputting the pulse output of the power feeding unit via a terminal 21. The rotational driving force of the motor 20 is transmitted through a reduction gear 22 including a harmonic gear shown in FIG.
To rotate. The shaft 23 transmits torque to the rotor drive gear of the jet engine.

FIG. 4 and FIG. 5 show the reduction gear 22 in detail. FIG. 4 shows a cross section of the drive unit. Motor 20
The rotational driving force of is transmitted to the harmonic gear 26 via the gears 24 and 25. The harmonic gear 26 includes a circular spline 27, a flex spline 28 that meshes with the circular spline 27, and the flex spline 28 is deformed via a bearing 30 so that the teeth of the flex spline 28 are partially and sequentially meshed with the circular spline 27. And a wave generator 29. The wave generator 29 is driven to rotate at high speed by the high-speed rotation driving force transmitted from the motor 20 via the gears 24 and 25, and the flex spline 28 is deformed accordingly, and the wave generator 2
The portion of the circular spline 27 that meshes with the flex spline 28 is sequentially rotated for every one rotation of 9, so that the low speed and high torque rotational driving force generated in the circular spline 27 is transmitted to the rotor of the jet engine. It The operation of the harmonic gear 26 will be described more specifically. The wave generator 29
Elliptical cam and ball bearing 3 fitted on its outer circumference
The inner ring of the bearing 30 is fixed to the cam, but the outer ring is elastically deformed via the balls. The flex spline 28 is a metal elastic body and has teeth carved on the outer periphery. The circular spline 27 has teeth with the same pitch as the flex spline on the inner circumference, and the number of teeth is two more than that of the flex spline 28. Due to the fact that the teeth of the flexspline 28 sequentially engage with the teeth of the circular spline 27 in accordance with the rotation of the wave generator 29, and the number of teeth differs by two when the engaging position makes one revolution. The flex spline 28 is rotated relative to the circular spline 27. Here, the wave generator 29 includes gears 24, 2.
5, the flexspline 28 is connected to the rotor of the jet engine via the shaft 23. Therefore, as the motor 20 rotates, the wave generator 29 rotates, and when the rotational driving force is transmitted to the flexspline 28, the rotational speed is significantly reduced, while the torque is significantly increased, and the decelerated rotational driving force is further increased. Will be transmitted to the rotor. As an example, the deceleration ratio is 1/600, the torque capacity is 2200 Kg. cm (maximum load value of harmonic gear) is preferable.

Next, a specific example of the mechanism for transmitting the rotational driving force from the drive unit to the drive unit of the jet engine will be described. The drive unit 18 transmits the rotational drive force to the drive shaft 33 of the accessory gear box 32 via the air starter drive pad or the manual crank pad 31. This rotational driving force is transmitted to the rotor 35 of the jet engine via the gear 34 in the accessory gear box 32. A blade 36 to be inspected is attached to the rotor 35.

Since the number of blades 36 and the load for rotating the rotor 35 are different depending on the type of engine, each stage of the compressor, and the turbine, the gearbox 32 is adapted to adapt the drive unit 18 thereto.
It is necessary to change the gear ratio and drive pad of the. Therefore, a microcomputer having a memory is provided, and its change data is accumulated as drive pulse number data of the pulse motor required to send one blade for each engine and stage. Based on the accumulated data, the microcomputer changes the gear ratio of the gear box and the drive pad or displays a change instruction. Further, the microcomputer reads the ON / OFF states of various switches of the control unit and displays the operating states of the switches on various indicators of the control unit together with the driving status of the pulse motor. Here, a 5 × 7 dot matrix display can be used as the display.

[0014]

As described above, according to the present invention, the rotational driving force generated by the pulse motor is decelerated by the harmonic gear to an extremely large degree and the torque is transmitted to the rotor of the jet engine. Can be downsized and the structure can be simplified.

[Brief description of drawings]

FIG. 1 is a diagram showing a power supply unit of a rotor rotating device for inspecting a turbine blade of a jet engine according to the present embodiment.

FIG. 2 is a diagram showing a control unit of the rotating device.

FIG. 3 is a diagram showing a drive unit of the rotating device.

FIG. 4 is a diagram showing a drive unit of the rotating device.

FIG. 5 is a diagram showing a structure of a harmonic gear of the drive unit.

FIG. 6 is a diagram showing a specific example of an accessory gear box used for transmitting a rotational driving force from a driving unit (driving unit) of the present invention to a jet engine rotor.

[Explanation of sign]

 20 pulse motor 26 harmonic gear 18 drive unit

Claims (6)

[Claims] 1. A high-speed 5-phase pulse motor rotational driving force generated; converts the high-speed rotation driving force of the pulse motor in the low speed and high torque rotational driving force, reduced in rotational driving force after the conversion
Together with the high pressure compressor of the jet engine
A harmonic gear that rotationally drives a jet engine rotor that bears a high rotational load ; and a pulse motor that drives the jet engine rotor through the harmonic gear in response to inspection work of a turbine blade or a compressor of the jet engine. A rotor rotating device for jet engine inspection, comprising a pulse motor driving unit for controllable continuous or intermittent rotation. 2. The harmonic gear includes a circular spline, a flex spline that meshes with the circular spline, and the flex spline is deformed through a bearing so that the teeth of the flex spline are partially and sequentially meshed with the circular spline. A wave generator, the wave generator is driven to rotate at a high speed by the pulse motor, the flex spline is deformed accordingly, and a circular spline meshed with the flex spline every one revolution of the wave generator. The jet engine according to claim 1, wherein the portions are sequentially rotated, and thereby the low speed and high torque rotational driving force generated in the circular spline is transmitted to the rotor of the jet engine. Emissions inspection rotor rotating device. 3. The rotor rotation for jet engine inspection according to claim 1, wherein the harmonic gear is small and lightweight and has a high reduction ratio and a high torque tolerance. apparatus. 4. The jet engine inspection rotor rotating device according to claim 1, wherein the pulse motor operates at a high speed and a low torque. 5. The pulse motor drive unit comprises a microcomputer having a memory for storing data relating to a plurality of jet engine types, and controls the drive of the pulse motor corresponding to a plurality of different types of engines. A rotor rotating device for jet engine inspection according to claim 1 or 4, characterized in that: 6. The rotor rotating apparatus for inspecting a jet engine according to claim 1, further comprising an indicator for displaying a stage name of a jet engine to be inspected.