Ignition voltage testing device for ignition electric nozzle of aero-engine

Abstract

The utility model discloses an ignition voltage testing device for an ignition electric nozzle of an aero-engine, which comprises a base, a sliding rod is fixedly arranged at the upper part of the base, and a first fixing device, a second fixing device and a third fixing device are sequentially nested on the sliding rod from top to bottom; the first fixing device, the second fixing device and the third fixing device can move on the sliding rod in a reciprocating mode and can be fixed to the sliding rod through fixing screws. An oil cup is installed on the first fixing device, an oil dripping nozzle is installed on the second fixing device, a testing clamp is installed on the third fixing device, the oil dripping nozzle is communicated with the oil cup through a pipeline, at least one electric adjusting valve is arranged on the pipeline, and an ignition electric nozzle to be tested is installed in the testing clamp. And the discharge end of the ignition electric nozzle to be tested corresponds to the oil dripping port of the upper oil dripping nozzle. According to the utility model, the engine combustion chamber environment can be simulated to the greatest extent, the actual ignition voltage used for assembling an ignition electric nozzle with an engine can be tested, the test is more accurate, and the feasibility is higher.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft engine plasma ignition test equipment, in particular to an ignition voltage test device for an aircraft engine ignition nozzle. Background Art

[0002] The ignition nozzle is installed in the engine combustion chamber, converting the transmitted high-voltage electrical pulses into an electric spark to ignite the fuel in the combustion chamber. Excessively high ignition nozzle voltage can cause the nozzle to misfire, resulting in engine starting failure. Therefore, the ignition nozzle's minimum ignition voltage is a critical indicator of the ignition nozzle and must be tested.

[0003] Conventional ignition nozzle firing voltage tests only measure the firing voltage in a laboratory environment, which is significantly different from the engine combustion chamber environment. This can cause the tested firing voltage to differ from the actual operating firing voltage, leading to ignition failure during actual use. Utility Model Content

[0004] The purpose of the utility model is to provide an ignition voltage test device for an aircraft engine ignition nozzle that can simulate the engine combustion chamber environment to the greatest extent possible and test the actual ignition voltage of the ignition nozzle used in the engine, with more accurate test results and higher reliability.

[0005] The utility model is achieved through the following technical solutions: a device for testing the ignition voltage of an aircraft engine ignition nozzle, comprising a base, a sliding rod fixedly provided on the upper part of the base, a first fixing device, a second fixing device, and a third fixing device nested in sequence from top to bottom on the sliding rod, the first fixing device, the second fixing device, and the third fixing device can all move back and forth on the sliding rod, and can all be fixed to the sliding rod by fixing screws; an oil cup is installed on the first fixing device, an oil drip nozzle is installed on the second fixing device, and a test fixture is installed on the third fixing device, the oil drip nozzle and the oil cup are connected by a pipeline, at least one electric regulating valve is provided on the pipeline, and the test fixture is used to install the ignition nozzle to be tested, and the discharge end of the ignition nozzle to be tested corresponds to the oil drip port of the upper oil drip nozzle.

[0006] The working principle of this technical solution is that the fuel in the combustion chamber is normally atomized, but in extreme cases it can condense into oil droplets. The ignition voltage test is performed under the most severe fuel and gas environment in the engine combustion chamber, namely, an oil-drip environment. This can maximize the simulation of the engine combustion chamber environment and test the actual ignition voltage of the ignition nozzle when assembled on the engine.

[0007] In order to better realize the present invention, further, the first fixing device, the second fixing device, and the third fixing device have the same structure, and are all composed of a sliding sleeve nested in the sliding rod and a fixing clip fixed to the sliding sleeve. The oil cup, oil drip nozzle, and test fixture are all fixed by the fixing clip and fixed to the sliding rod by fixing screws installed on the sliding sleeve.

[0008] In order to better realize the present invention, further, a calibration rod parallel to the sliding rod is provided on the bottom plate, and a scale is provided on the calibration rod.

[0009] In order to better realize the present invention, further, the oil cup is filled with RP-3 aviation kerosene, and the RP-3 aviation kerosene is added to 2 / 3 of the capacity of the oil cup. A cup cover detachably connected to the oil cup is also provided on the top of the oil cup.

[0010] In order to better realize the present invention, further, the dripping speed of the oil dripping nozzle is 10 drops / min to 100 drops / min, and the diameter of the dripping oil droplets is Φ2mm to Φ5mm.

[0011] In order to better implement the present invention, further, the base is rectangular, and four leveling screws are provided on the base.

[0012] In order to better implement the present invention, further, the four corners of the base are all rounded.

[0013] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0014] (1) Compared with the previous aircraft engine ignition nozzle ignition voltage test, the present invention simulates the engine combustion chamber environment to the greatest extent and tests the actual ignition voltage of the ignition nozzle used in the engine. The test results are more accurate and reliable than the previous aircraft engine nozzle ignition voltage test;

[0015] (2) The utility model has a simple structure and is easy to operate. Non-professional technicians can also quickly start testing the ignition nozzle. It is highly practical and suitable for wide promotion and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0017] Figure 1 It is a schematic diagram of the planar structure of the present utility model.

[0018] Among them: 1-base, 2-sliding rod, 3-first fixing device, 4-second fixing device, 5-third fixing device, 6-fixing screw, 7-oil cup, 8-oil drip nozzle, 9-test fixture, 10-electric regulating valve, 11-calibration rod, 12-leveling screw. DETAILED DESCRIPTION

[0019] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0020] In the description of this utility model, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; direct connections, indirect connections through an intermediate medium, or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on the specific circumstances.

[0021] Example 1:

[0022] The main structure and principle of this embodiment are as follows: Figure 1 As shown, it includes a base 1, a sliding rod 2 is fixedly provided on the upper part of the base 1, and the sliding rod 2 is nested with a first fixing device 3, a second fixing device 4, and a third fixing device 5 from top to bottom. The first fixing device 3, the second fixing device 4, and the third fixing device 5 can all move back and forth on the sliding rod 2, and can all be fixed to the sliding rod 2 by fixing screws 6; an oil cup 7 is installed on the first fixing device 3, an oil drip nozzle 8 is installed on the second fixing device 4, and a test fixture 9 is installed on the third fixing device 5. The oil drip nozzle 8 and the oil cup 7 are connected by a pipeline, and at least one electric regulating valve 10 is provided on the pipeline. The test fixture 9 is used to install the ignition nozzle to be tested, and the discharge end of the ignition nozzle to be tested corresponds to the oil drip port of the upper oil drip nozzle 8.

[0023] The specific process of using the test device to test the ignition voltage of the ignition nozzle for an aircraft engine includes the following steps:

[0024] S1: Install the ignition nozzle under test: Install the ignition nozzle under test on the test fixture 9;

[0025] S2: Connect the ignition nozzle to be tested to a power supply, and the power supply should have an adjustable output voltage;

[0026] S3: According to the test conditions, adjust the oil dripping speed and oil dripping ball diameter of the oil dripping device;

[0027] S4: operate the electric regulating valve 9 to control the oil dripping nozzle 8 to drip fuel to the discharge end of the ignition nozzle under test;

[0028] S5: Set the power supply output voltage V i , supply power to the ignition nozzle under test and observe whether the ignition is ignited;

[0029] S6: Set the power supply output voltage V i+1 ，V i+1 = V i + V step ，V step is the step length, power the ignition nozzle under test and observe whether the ignition is ignited;

[0030] S7: Repeat steps S5 and S6 until the ignition nozzle under test ignites. The voltage at this time is V i This is the ignition voltage of the ignition nozzle being tested.

[0031] Example 2:

[0032] Based on the above embodiment, this embodiment further defines the structures of the first fixing device 3, the second fixing device 4, and the third fixing device 5, such as Figure 1 As shown, the first fixing device 3, the second fixing device 4, and the third fixing device 5 have the same structure, each consisting of a sliding sleeve nested in the sliding rod 2 and a fixing clamp fixed to the sliding sleeve. The oil cup 7, oil drip nozzle 8, and test fixture 9 are all fixed by the fixing clamp and fixed to the sliding rod 2 by fixing screws 6 installed on the sliding sleeve. The rest of this embodiment is the same as the above embodiment and will not be repeated here.

[0033] Example 3:

[0034] On the basis of the above embodiment, this embodiment further adds a calibration rod 11, such as Figure 1 As shown, the base plate 1 is also provided with a calibration rod 11 parallel to the slide bar 2, and is provided with a scale. Due to the corresponding positional relationships among the oil cup 7, the oil drip nozzle 8, and the test fixture 9, and in particular the need for the oil drip nozzle 8 to be aligned with the discharge port of the ignition nozzle to be tested, the calibration rod 11 is specifically provided to facilitate calibration and marking of the fixing positions of the first fixing device 3, the second fixing device 4, and the third fixing device 5, thus facilitating the assembly of the entire test device. The remainder of this embodiment is identical to the previous embodiment and will not be further elaborated here.

[0035] Example 4:

[0036] This embodiment, based on the above embodiment, further defines an oil cup 7. The oil cup 7 is filled with RP-3 aviation kerosene, which is filled to two-thirds of its capacity. A removable lid is also provided on top of the oil cup 7. The open top of the oil cup 7 facilitates the addition of RP-3 aviation kerosene. Furthermore, the removable lid, which seals the top opening of the oil cup 7 and is removably connected to the oil cup 7, prevents the external environment from adversely affecting the RP-3 aviation kerosene in the oil cup 7, such as preventing dust from entering and affecting the test process and results. The remainder of this embodiment is identical to the above embodiment and will not be further elaborated here.

[0037] Example 5:

[0038] This embodiment, based on the above embodiment, further refines the oil drip nozzle 8. The drip rate of the oil drip nozzle 8 is 10 to 100 drops / min, and the diameter of the oil droplets is 2 to 5 mm. To better test the ignition voltage of the ignition nozzle, the drip rate of the oil drip nozzle 8 is preferably 10 to 100 drops / min, and the diameter of the oil droplets is 2 to 5 mm. The rest of this embodiment is the same as the above embodiment and will not be repeated here.

[0039] Example 6:

[0040] This embodiment, based on the previous embodiment, further defines the structure of base 1. Base 1 is rectangular and has four leveling screws 12 installed on each side. Leveling screws 12 are primarily designed to ensure the stability of the entire test device, facilitating optimal ignition voltage testing of the ignition nozzle. The remainder of this embodiment is identical to the previous embodiment and will not be further elaborated here.

[0041] Example 7:

[0042] Based on the above embodiment, this embodiment further defines the structure of the base 1, and the four corners of the base 1 are all rounded. The rest of this embodiment is the same as the above embodiment and will not be repeated here.

[0043] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A device for testing the ignition voltage of an aircraft engine ignition nozzle, characterized in that: The invention comprises a base (1), wherein a slide bar (2) is fixedly provided on the upper part of the base (1), and a first fixing device (3), a second fixing device (4), and a third fixing device (5) are nested in the slide bar (2) from top to bottom in sequence, and the first fixing device (3), the second fixing device (4), and the third fixing device (5) can all move back and forth on the slide bar (2) and can all be fixed to the slide bar (2) by fixing screws (6); an oil cup (7) is installed on the first fixing device (3), an oil drip nozzle (8) is installed on the second fixing device (4), and a test fixture (9) is installed on the third fixing device (5), the oil drip nozzle (8) and the oil cup (7) are connected by a pipeline, and at least one electric regulating valve (10) is provided on the pipeline, and the test fixture (9) is used to install an ignition nozzle to be tested, and the discharge end of the ignition nozzle to be tested corresponds to the oil dripping port of the upper oil drip nozzle (8).

2. The ignition voltage test device for an aircraft engine ignition nozzle according to claim 1, characterized in that: The first fixing device (3), the second fixing device (4), and the third fixing device (5) have the same structure, and are all composed of a sliding sleeve nested in the sliding rod (2) and a fixing clamp fixed to the sliding sleeve. The oil cup (7), the oil drip nozzle (8), and the test fixture (9) are all fixed by the fixing clamp and fixed to the sliding rod (2) by a fixing screw (6) installed on the sliding sleeve.

3. The ignition voltage test device for an aircraft engine ignition nozzle according to claim 1 or 2, characterized in that: The bottom plate (1) is also provided with a calibration rod (11) parallel to the slide rod (2), and a scale is provided on the calibration rod (11).

4. The ignition voltage test device for an aircraft engine ignition nozzle according to claim 1 or 2, characterized in that: The oil cup (7) is filled with RP-3 aviation kerosene, and the RP-3 aviation kerosene is added to 2 / 3 of the capacity of the oil cup (7). The top of the oil cup (7) is also provided with a cup cover that is detachably connected to the oil cup (7).

5. The ignition voltage test device for an aircraft engine ignition nozzle according to claim 1 or 2, characterized in that: The oil dripping speed of the oil dripping nozzle (8) is 10 drops / min to 100 drops / min, and the diameter of the oil droplets dripping out is Φ2mm to Φ5mm.

6. The ignition voltage test device for an aircraft engine ignition nozzle according to claim 1 or 2, characterized in that: The base (1) is rectangular, and four leveling screws (12) are provided on each of the four sides of the base (1).

7. The ignition voltage test device for an aircraft engine ignition nozzle according to claim 1 or 2, characterized in that: The four corners of the base (1) are all rounded.

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