CN103075987A - Device for dynamically measuring aeroengine nozzle diameter - Google Patents

Abstract

The invention belongs to the field of aeroengines, and in particular relates to a device for dynamically measuring the aeroengine nozzle diameter. The device comprises an angle displacement sensor 5, a wire spool 4, a steel wire rope 3, a steel wire rope fixing device 2 and a computer 9. The device is tested in products already, is commonly used by a plurality of important model researches and high altitude simulation tests of aeroengines in China, and plays a significant role. According to the technical scheme, very common and less elements and materials are included, and a system is very simple and easy to realize. Practices test that the device works reliably, is stable and flexible in system and can dynamically monitor and measure the aeroengine nozzle diameter during the whole course in real time. The diameter measurement precision reaches above 0.1mm, and engine thrust measurement requirements can be completely satisfied.

Description

A kind of aeromotor nozzle diameter dynamic measurement device

Technical field

The invention belongs to the aeromotor field, particularly relate to a kind of aeromotor nozzle diameter dynamic measurement device.

Background technology

Along with the development and progress of aeromotor, turbojet and turbofan jet pipe develop into present adjustable receipts by the fixedly contracting nozzle at the beginning of last century and expand jet pipe (Laval nozzle) and vector spray.

When adjustable receipts expand the jet pipe engine and carry out altitude simulation test, must be dynamically/area (that is, nozzle diameter) of engine nozzle measured in real time, for the correction of engine measuring thrust.As not carrying out this thrust correction, measure thrust and will have larger error with actual aerial thrust.Therefore, when adjustable receipts expansion jet pipe engine carried out altitude simulation test, dynamically/in real time Measurement accuracy of engine nozzle area was absolutely necessary.

The measurement of engine nozzle diameter more easily realizes in the engine stationary state, can use general linear dimension survey instrument to measure, and also can adopt some patented product to measure.Such as " a kind of measuring tool of adjustable convergence jet size ", the measurement of nozzle diameter when just being suitable for on-wing maintenance.

In running order when engine, namely adjustable receipts expansion jet pipe is in when magnifying with deflated state, dynamically/there is certain difficulty in Measurement accuracy engine nozzle diameter in real time.At present, domestic engine design and manufacturings side, all bar none employing is installed near the feedback transducer of engine nozzle adjustment sheet drive unit and carries out monitoring and the measurement of nozzle diameter.This method, on the one hand, precision is not high; On the other hand, if at the voltage isolation module of the input/output terminal improper use of feedback transducer, will cause harmful effect to the engine tail nozzle regulating system; The 3rd, if with engine feedback transducer access altitude simulation test equipment, can affect the independence of tested object.

In the process of the test, realize the real-time measurement of engine nozzle diameter, in theory, can also use some noncontact measuring methods, such as shooting, laser, the method such as infrared, but these method costs are high, and some precision is inadequate, some measurement range is less, does not also generally drop into Practical in technical field of engines.

Summary of the invention

Goal of the invention: a kind of aeromotor nozzle diameter dynamic measurement device is provided, when adjustable receipts expansion jet pipe engine carries out altitude simulation test, is used for measurement and the correction of engine Thrust.

Technical scheme: a kind of aeromotor nozzle diameter dynamic measurement device, compriseangular displacement sensor 5,wire spool 4,wire rope 3, wire rope fixing device 2, computing machine 9, one end ofwire rope 3 links to each other with engine nozzle 1 by wire rope fixing device 2, the other end ofwire rope 3 is fixed on thewire spool 5, and be wrapped in the annular wire casing ofwire spool 5,wire spool 5 is connected into one by flat key and angular displacementsensor output shaft 6 and does the synchronous rotary motion withangular displacement sensor 5,angular displacement sensor 5 bodies are installed near the engine on actionless equipment or the basis by angulardisplacement sensor holder 7, and cable 8 links to each other the signal output part ofangular displacement sensor 5 with computing machine 9.

The size ofwire spool 5 diameters is adjusted according to engine nozzle 1 diameter.

Wire rope 3 is positioned on the extended line of engine nozzle 1 radius.

Beneficial effect: process checking in product of the present invention, for the common employing of development and altitude simulation test institute of the many important models of China's aeromotor, played vital role.Technical scheme of the present invention, it is very common to comprise element and material, and quantity is few, and system is very simple, is easy to realize.Through practice test, reliable operation, system stability, sensitivity can realize whole process, real-time dynamic monitoring and the measurement of engine nozzle diameter.Diameter measurement precision of the present invention reaches more than the 0.1mm, can satisfy the needs that motor power is measured fully.

Description of drawings

Fig. 1 is principle of the invention synoptic diagram.The title of each parts and effect are as follows among the figure:

1---engine nozzle, measurand.

2---wire rope fixing device is used for an end and the engine jet pipe adjustment sheet of wire rope are carried out positive connection.

3---wire rope, one of device critical elements.

4---wire spool, one of device critical elements is with the coaxial positive connection of angular displacement sensor.

5---angular displacement sensor, install important measuring sensor, rotate synchronously with wire spool.

6---the angular displacement sensor output shaft, for installation and the location of wire spool.

7---the angular displacement sensor holder, keep forbidding, be used for fixed angles displacement transducer body, bear reactive torque.

8---cable, realize the signal transmission of angular displacement sensor and computing machine.

9---computing machine, carry out collection, processing, demonstration and the printing of measurement data.

Embodiment

Below in conjunction with accompanying drawing the present invention is done to describe in further detail, see also Fig. 1.

A kind of aeromotor nozzle diameter dynamic measurement device, compriseangular displacement sensor 5,wire spool 4,wire rope 3, wire rope fixing device 2, computing machine 9, one end ofwire rope 3 links to each other with engine nozzle 1 by wire rope fixing device 2, the other end ofwire rope 3 is fixed on thewire spool 5, and be wrapped in the annular wire casing ofwire spool 5,wire spool 5 is connected into one by flat key and angular displacementsensor output shaft 6 and does the synchronous rotary motion withangular displacement sensor 5,angular displacement sensor 5 bodies are installed near the engine on actionless equipment or the basis by angulardisplacement sensor holder 7, and cable 8 links to each other the signal output part (being generally 0VDC～10VDC voltage signal) ofangular displacement sensor 5 with computing machine 9.

By this device, in the time of engine nozzle 1 can being shunk or enlarges, nozzle diameter changes the rectilinear motion on radial direction, is converted into rotatablely moving ofangular displacement sensor 5, thereby realizes utilizingangular displacement sensor 5 to reach kinetic measurement or following the purpose that nozzle diameter changes.

Need the extreme variations scope according to nozzle diameter, the size ofwire spool 5 diameters is adjusted according to engine nozzle 1 diameter.Selecting suitable wire spool diameter, is the variation range that the anglec of rotation contains nozzle diameter with the measurement range that guaranteesangular displacement sensor 5.

When system installs, must adjust the start angle of angular displacement sensor rotation, and utilize the elastic torsion moment of angular displacement sensor itself, wire rope is tightened.Wire rope 3 is positioned on the extended line of engine nozzle 1 radius.

During use, before system comes into operation, also be that engine is in dead ship condition, need system is demarcated.That is, use special spout to handle oil sources, open step by step or shrink engine nozzle 1, measure the diameter of engine nozzle 1 with the linear dimension survey instrument, and record simultaneously the output signal value of the correspondingangular displacement sensor 5 of each measurement diameter with computing machine 9.Like this, by static demarcating, just can obtain the corresponding relation between engine nozzle 1 diameter (being area) andangular displacement sensor 5 readings (voltage signal amount).During the engine altitude simulation test, the electric signal thatangular displacement sensor 5 is exported concerns that by the diameter of demarcating the engine nozzle 1 that obtains-electric signal the diameter dimension that is scaled engine nozzle 1 gets final product, thus measurement and the tracking of realization engine nozzle 1 diameter.

Technical scheme is: on same diameter, and each symmetrical this measurement mechanism of cover of installing.The position of diameter is chosen, preferential recommended levels diameter or close horizontal diameter.The final value of engine nozzle diameter is got two and is measured the average of diameter.

Major advantage is: two measuring points are arranged, and 1. two measuring point datas can be compared mutually, can be used for judging whether measurement mechanism is in correct, reliable duty; 2. in the engine test process, in case certain measuring point breaks down, engine can continue test, especially, for some for measuring the less demanding test of thrust.Sometimes, this point is very important, because, the system and program of altitude simulation test is very complicated, if fault is got rid of, must carry out first engine cut-off, system cools, after a series of preliminary works such as the lid that opens the cabin, could carry out real troubleshooting work, waste a large amount of time and the energy.

Embodiment one

On same diameter, each symmetrical this measurement mechanism of cover of installing.The position of diameter is chosen, preferential recommended levels diameter or close horizontal diameter.The final value of engine nozzle diameter is got two and is measured the average of diameter.Present embodiment has two measuring points, and two measuring point datas can be compared mutually, can be used for judging whether measurement mechanism is in correct, reliable duty; In the engine test process, in case certain measuring point breaks down, engine can continue test, especially, for some for measuring the less demanding test of thrust.Sometimes this point is extremely important, because, the system and program of altitude simulation test is very complicated, if fault is got rid of, must carry out first engine cut-off, system cools, after a series of preliminary works such as the lid that opens the cabin, real troubleshooting work could be carried out, a large amount of time and the energy be wasted.

Embodiment two

Each symmetrical this measurement mechanism of cover, totally 4 cover installed on the diameter of two right-angled intersections.The position of diameter is chosen, recommended levels and vertical, or near.The final value of engine nozzle diameter is got 4 and is measured the average of diameter.Present embodiment has 4 measuring points, and measuring accuracy is higher.

Claims (3)

1. aeromotor nozzle diameter dynamic measurement device, it is characterized in that, comprise angular displacement sensor [5], wire spool [4], wire rope [3], wire rope fixing device [2], computing machine [9], one end of wire rope [3] links to each other with engine nozzle [1] by wire rope fixing device [2], the other end of wire rope [3] is fixed on the wire spool [5], and be wrapped in the annular wire casing of wire spool [5], wire spool [5] is connected into one by flat key and angular displacement sensor output shaft [6] and does the synchronous rotary motion with angular displacement sensor [5], angular displacement sensor [5] body is installed near the actionless equipment of engine or the basis by angular displacement sensor holder [7], and cable 8 links to each other the signal output part of angular displacement sensor [5] with computing machine [9].

2. a kind of aeromotor nozzle diameter dynamic measurement device according to claim 1 is characterized in that, the size of wire spool [5] diameter is adjusted according to engine nozzle [1] diameter.

3. a kind of aeromotor nozzle diameter dynamic measurement device according to claim 2 is characterized in that wire rope [3] is positioned on the extended line of engine nozzle [1] radius.

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