Detection device for over-rotation protection executing mechanism of aviation turboshaft engine

Abstract

An aviation turbine shaft engine over-rotation protection execution mechanism detection device comprises an oil way system and a control circuit, and the oil way system comprises an oil tank, a direct-current electric pump and a two-position three-way electromagnetic valve; a normally open loop of the electric pump and the electromagnetic valve and the oil tank form a circulating oil path through an oil pipe; a normally closed loop of the electromagnetic valve is connected with an oil inlet of the aviation turboshaft engine over-rotation protection execution mechanism test piece, and an oil outlet of the over-rotation protection execution mechanism test piece is connected with the oil tank through an oil pipe; the control circuit comprises a power switch, a detection switch and a two-position three-way electromagnetic valve; the power switch controls power supply of the direct-current electric pump, and the detection switch controls power supply of a control coil of the two-position three-way electromagnetic valve and a test piece of the aviation turbine shaft engine over-rotation protection executing mechanism. According to the utility model, an integrated box type design is adopted, the size is small, the structure is simple, an onboard direct current 27V power supply is used for supplying power, the external field use requirement of a helicopter can be met, and the working condition of an aviation turbine shaft engine over-rotation protection executing mechanism can be conveniently detected.

Description

TECHNICAL FIELD

[0001] The utility model relates to an aviation turbine shaft engine over-speed protection actuating mechanism ground detection device for detecting the working condition of the engine over-speed protection actuating mechanism on the ground. BACKGROUND

[0002] The over-speed protection actuating mechanism of the aviation turbine shaft engine assembled on the certain type of helicopter is mainly used for cutting off the oil supply to the engine combustion chamber through rapid cutting after the free turbine speed of the engine exceeds the limited value, so that the engine is stopped and the protection of the engine is realized.

[0003] Therefore, it is necessary to design an aviation turbine shaft engine over-speed protection actuating mechanism working condition ground detection device for the usual use and maintenance of the helicopter to ensure that the over-speed protection actuating mechanism works normally.

[0004] Currently, there is no such detection device, which brings great inconvenience to the usual use and maintenance of the helicopter. INVENTION CONTENTS

[0005] The utility model in the background of the problem, according to the working principle of over-speed protection actuating mechanism, proposes an aviation turbine shaft engine over-speed protection actuating mechanism detection device, which can well meet the field use requirements of the helicopter.

[0006] The technical scheme adopted by the utility model is:

[0007] An aviation turbine shaft engine over-speed protection actuating mechanism detection device, comprising an oil circuit system and a control circuit, the oil circuit system comprising an oil tank (1), a direct-current electric pump (11) and a two-position three-way electromagnetic valve (12); the normally open circuit of the direct-current electric pump (11) and the two-position three-way electromagnetic valve (12) is connected in series with the oil tank through an oil pipe to form a circulating oil circuit; the normally closed circuit outlet of the two-position three-way electromagnetic valve (12) is connected to the oil inlet of an aviation turbine shaft engine over-speed protection actuating mechanism test piece, and the oil outlet of the aviation turbine shaft engine over-speed protection actuating mechanism test piece is connected to the oil tank (1) through an oil pipe;

[0008] The control circuit comprises a power switch (5), a detection switch (3) and a two-position three-way electromagnetic valve (12); the power switch (5) controls a power supply circuit connected with a direct current electric pump (11); the detection switch (3) controls a control coil of the two-position three-way electromagnetic valve (12) and a power supply circuit of an aviation turbine shaft engine overspeed protection actuator test piece.

[0009] The aviation turbine shaft engine overspeed protection actuator detection device is provided with an overflow valve (13) in the oil circuit system; an inlet of the overflow valve (13) is connected with a normally closed circuit outlet of the two-position three-way electromagnetic valve (12); and an overflow port of the overflow valve (13) is connected with the oil tank (1) through a pipeline.

[0010] The aviation turbine shaft engine overspeed protection actuator detection device comprises a shell, an oil circuit system and a control circuit arranged in the shell; a detection platform (9) is arranged on the upper portion of the shell; an overspeed protection actuator test piece fixing stud (10) is arranged on the detection platform (9); and a control switch and an oil outlet connector (8) are arranged on the shell.

[0011] The aviation turbine shaft engine overspeed protection actuator detection device is provided with a power indicator lamp (4) connected with a power supply circuit of the direct current electric pump (11); and a normally closed circuit outlet of the two-position three-way electromagnetic valve (12) is connected with a pressure signaler (14) in an aviation turbine shaft engine overspeed protection actuator test circuit.

[0012] The aviation turbine shaft engine overspeed protection actuator detection device is provided with an open or closed oil tank; the oil tank is integrally connected with the device shell in parallel or arranged on one side in the shell; and an oil outlet of an aviation turbine shaft engine overspeed protection actuator test piece is connected with the oil tank (1) through an oil pipe.

[0013] The utility model has the advantages of small size, simple structure, on-machine direct current 27V power supply, and good satisfaction of the requirement of helicopter field use.

[0014] 1. The aviation turbine shaft engine overspeed protection actuator detection device mainly comprises an oil tank, a direct current electric pump and a two-position three-way electromagnetic valve, adopts an integrated tank type design, has small size and simple structure, uses on-machine direct current 27V power supply, and can well satisfy the requirement of helicopter field use.

[0015] 2. The aviation turbine shaft engine overspeed protection actuator detection device is provided with an overflow valve; when an actuator oil circuit is not open, the overflow valve can make oil return to the oil tank, so as to ensure the safety of the oil circuit.

[0016] 3, The utility model discloses a kind of aviation turbine shaft engine over-speed protection actuator detection devices, can conveniently outside field regularly detect the working condition of aviation turbine shaft engine over-speed protection actuator, promptly find and eliminate fault, to ensure that it always maintains good working condition in the whole use cycle of engine. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 As shown in the utility model detection device overall structure schematic diagram (external);

[0018] Figure 2 As shown in the utility model detection device oil circuit system diagram (working principle);

[0019] Figure 3 As shown in the utility model detection device control circuit circuit principle diagram.

[0020] In the drawing, mark 1, open oil tank, 2, pressure display instrument, 3, detection switch, 4, power indicator light, 5, power switch, 6, power socket, 7, cable plug, 8, oil outlet joint, 9, detection platform, 10, over-speed protection actuator test piece fixed stud, 11, direct current electric pump, 12, two-position three-way electromagnetic valve, 13, overflow valve, 14, pressure signaler. DETAILED DESCRIPTION

[0021] To make the technical concept and the advantage of the utility model creation realize its practical new purpose more clearly, the technical scheme of the utility model is further described in detail below in conjunction with the drawings. It should be understood that the following examples are only used to explain and illustrate the preferred embodiment of the utility model, and should not be regarded as and constitute the limitation to the patent protection scope required by the utility model. EMBODIMENT

[0022] Referring to Figures 1-3 The utility model aviation turbine shaft engine over-speed protection actuator detection device, including oil circuit system and control circuit, the oil circuit system includes oil tank 1, direct current electric pump 11, two-position three-way electromagnetic valve 12;The normally open circuit of direct current electric pump 11 and two-position three-way electromagnetic valve 12 is connected with oil tank by oil pipe series and forms circulating oil circuit;The normally closed circuit outlet of two-position three-way electromagnetic valve 12 is connected with the oil inlet of aviation turbine shaft engine over-speed protection actuator test piece, and the oil outlet of aviation turbine shaft engine over-speed protection actuator test piece is connected with oil tank 1 by oil pipe;

[0023] The control circuit comprises a power switch 5, a detection switch 3 and a two-position three-way electromagnetic valve 12; the power switch 5 is connected to the power supply circuit of the DC electric pump 11 (controlling the power on-off of the power supply of the DC electric pump, the power supply of the DC electric pump 11 is turned on before detection, and the DC electric pump 11 works to prepare for detection), the detection switch 3 is connected to the control coil of the two-position three-way electromagnetic valve 12 and the power supply circuit of the over-speed protection actuator test piece of the aero turbine shaft engine, and controls the power on-off of the two-position three-way electromagnetic valve 12 and the over-speed protection actuator test piece of the aero turbine shaft engine (the power supply of the over-speed protection actuator test piece is provided through the cable connector 7).

[0024] Working principle: when working, the power switch 5 is turned on, the DC electric pump sucks oil from the bottom of the oil tank, and the oil is led to the two-position three-way electromagnetic valve; when the test button (detection switch 3) is not pressed, the oil inlet of the two-position three-way electromagnetic valve is communicated with the oil return path (the normally open outlet), and the oil from the DC electric pump returns to the oil tank; when the detection switch 3 is pressed, the two-position three-way electromagnetic valve acts, the normally open outlet is closed, the normally closed outlet is opened, the oil inlet is communicated with the oil path of the normally closed outlet, and the oil is sent to the over-speed protection actuator test piece through the oil pipe and the oil outlet connector 8; if the test piece works normally at this time, the oil inlet and outlet are communicated, the oil flows back to the oil tank along the pipeline, and the detection process is completed. Embodiment

[0025] Reference Figure 2 The difference between the embodiment and embodiment 1 is that: in order to avoid the fault of the over-speed protection actuator test piece of the aero turbine shaft engine (the execution oil path is not communicated) causing the oil path fault of the detection device (the oil pipe is blocked or broken, causing the oil to be sprayed), an overflow valve 13 is arranged in the oil path system, the inlet of the overflow valve 13 is connected to the normally closed outlet of the two-position three-way electromagnetic valve 12, and the overflow port of the overflow valve 13 is connected to the oil tank 1 through a pipeline. Once the over-speed protection actuator test piece cannot work normally, the detection circuit oil flows back to the oil tank through the overflow valve. In this case, an alarm can be set through a pressure display instrument. Embodiment

[0026] Reference Figures 1-3 The difference between the over-speed protection actuator detection device of the aero turbine shaft engine of the embodiment and embodiment 1 is that: a housing is arranged, the oil path system and the control circuit are arranged in the housing, a detection platform 9 is arranged on the upper part of the housing, an over-speed protection actuator test piece fixing stud 10 (used for fixing the actuator during detection) is arranged on the detection platform 9, and a control switch and an oil outlet connector 8 are arranged on the housing. The control switch comprises a power switch 5 and a detection switch 3.

[0027] The direct current electric pump 11 is connected with a power indicator lamp 4 in a power supply circuit, and a normally closed circuit outlet of a two-position three-way electromagnetic valve 12 in a test circuit of an aviation turbine shaft engine overspeed protection actuator is connected with a pressure signaler 14, which can be a pressure sensor, and an output signal of the pressure sensor is connected with a pressure display instrument 2; the pressure signaler can be a common mechanical pressure gauge, and the power indicator lamp 4 and the pressure display instrument 2 (or the pressure gauge) are arranged in a device housing.

[0028] As shown in Figure 1 The aviation turbine shaft engine overspeed protection actuator detection device, an open oil tank (or a closed oil tank) is arranged in parallel with the device housing and is integrally connected with the device housing or is arranged on one side in the device housing, an oil outlet of the aviation turbine shaft engine overspeed protection actuator (a test piece) is connected with the oil tank 1 through an oil return pipe, and the other end of the oil return pipe is integrally arranged with the oil tank 1.

[0029] The aviation turbine shaft engine overspeed protection actuator detection device has the advantages of small size, simple structure, and the like, can be powered by a 27V direct current power supply on an aircraft (through a power socket 6), can well meet the requirements of field use of a helicopter, can facilitate regular detection of the engine overspeed protection actuator, and can eliminate safety hazards in time.

[0030] Of course, the above only describes the preferred embodiments of the present application, and does not constitute a limitation on the present application. Those skilled in the art can make other modifications to the embodiments of the present application without creative labor under the guidance of the prior art, and any modification or simple replacement or equivalent replacement made within the spirit and principles of the present application by using the conventional technical means in the art should be included in the protection scope of the present application.

Claims

1. An over-speed protection actuator detection device for an aero turbine shaft engine, comprising an oil circuit system and a control circuit, characterized in that: The oil circuit system comprises an oil tank (1), a direct current electric pump (11), and a two-position three-way electromagnetic valve (12); a normally open circuit of the direct current electric pump (11) and the two-position three-way electromagnetic valve (12) forms a circulating oil circuit with the oil tank through an oil pipe; an outlet of a normally closed circuit of the two-position three-way electromagnetic valve (12) is connected to an oil inlet of an aero turbine shaft engine over-speed protection actuator test piece, and an oil outlet of the aero turbine shaft engine over-speed protection actuator test piece is connected to the oil tank (1) through an oil pipe. The control circuit comprises a power switch (5), a detection switch (3), and the two-position three-way electromagnetic valve (12); the power switch (5) controls a power supply circuit connected to the direct current electric pump (11), and the detection switch (3) controls a control coil of the two-position three-way electromagnetic valve (12) and a power supply circuit of the aero turbine shaft engine over-speed protection actuator test piece.

2. The aircraft turbo-shaft engine overspeed protection actuator detection apparatus of Claim 1, wherein: The oil circuit system is provided with an overflow valve (13), an inlet of the overflow valve (13) is connected to an outlet of the normally closed circuit of the two-position three-way electromagnetic valve (12), and an overflow port of the overflow valve (13) is connected to the oil tank (1) through a pipe.

3. The aero turbine shaft engine overspeed protection actuator detection device according to claim 1 or 2, characterized in that: The oil circuit system comprises a housing, an oil circuit system, and a control circuit arranged in the housing, a detection platform (9) is arranged on an upper portion of the housing, an over-speed protection actuator test piece fixing stud (10) is arranged on the detection platform (9), and a control switch and an oil outlet joint (8) are arranged on the housing.

4. The turbo-shaft engine overspeed protection actuator detection apparatus of claim 3, wherein: A power indicator lamp (4) is connected in a power supply circuit of the direct current electric pump (11), and a pressure signaler (14) is connected to an outlet of the normally closed circuit of the two-position three-way electromagnetic valve (12) in an aero turbine shaft engine over-speed protection actuator test circuit.

5. The turbo-shaft engine overspeed protection actuator detection apparatus of claim 3, wherein: The oil tank (1) is an open or closed oil tank, which is integrally connected to the device housing side by side or arranged on one side in the housing, and an oil outlet of the aero turbine shaft engine over-speed protection actuator test piece is connected to the oil tank (1) through an oil pipe.

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