Water spraying equipment and method for aircraft engine water swallowing test

Abstract

The present application belongs to the technical field of aircraft engine water swallowing test, and specifically relates to an aircraft engine water swallowing test water spraying equipment and method thereof, wherein the equipment includes: a supporting frame, which is rectangular, with a hollow bottom edge, a water supply connector at one end, a plurality of water supply connection holes on the front side wall, and a plurality of pairs of forward support rod fixing supports on the two side edges; a plurality of water spray pipes, with both ends bent backward, connected to the top edge and the bottom edge of the supporting frame with quick-release joints, and connected to each water supply connection hole; the side wall of each water spray pipe has a plurality of pairs of water spray holes facing the two side edges of the supporting frame; the side wall of each water spray pipe has a plurality of rear support rod fixing supports; a plurality of support rods; a plurality of pairs of support rod forward fixing clamps, which are bolted to each pair of forward support rod fixing supports and clamp the two ends of each support rod; a plurality of groups of support rod rear fixing clamps, which are bolted to each row of rear support rod fixing supports and clamp the side walls of each water spray pipe.

Description

Technical Field

[0001] The present application belongs to the technical field of aero-engine water swallowing test, and specifically relates to a water spraying device and method for aero-engine water swallowing test. Background Art

[0002] When an aircraft flies in the rain, the aircraft engine will swallow a large amount of rainwater, causing friction damage between the casing and the blades, or even surge and flameout, seriously affecting the flight safety of the aircraft. For this reason, the aircraft engine finalization assessment test stipulates a water swallowing test to assess the working ability of the aircraft engine after swallowing rainwater and to test the performance of the aircraft engine after swallowing rainwater, so as to discover and eliminate safety hazards before the test flight.

[0003] Currently, when conducting aircraft engine water ingestion tests, water spray equipment consisting of multiple sets of water supply pipelines and atomizing nozzles adopts a direct injection layout, spraying water directly at the aircraft engine inlet to simulate the actual situation of aircraft swallowing rainwater and thus evaluate aircraft engine performance. This technical solution has the following shortcomings:

[0004] 1) The system consists of multiple sets of water supply pipes and atomizing nozzles, resulting in a complex piping structure that is difficult to disassemble and assemble. Using universal water supply pipes and atomizing nozzles makes it difficult to meet the requirements of different aircraft engine models for water ingestion tests regarding water particle size, flow rate, and distribution.

[0005] 2) A direct injection layout is used, with water sprayed directly toward the aircraft engine inlet. The sprayed liquid water is parallel to the aircraft engine intake direction, has a certain axial initial velocity, and enters the aircraft engine directly, creating additional loads.

[0006] 3) To avoid excessive disturbance to the aircraft engine intake and thus distortion of the aircraft engine intake, the water spray equipment needs to be far away from the aircraft engine inlet. The sprayed liquid water is greatly affected by the aircraft engine intake airflow field, tends to shrink centrally, and is concentrated in the center of the aircraft engine. Almost all of it will be sucked into the interior of the aircraft engine, causing excessive water inhalation.

[0007] This application is proposed in view of the above-mentioned technical defects.

[0008] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present application. In the absence of clear evidence that the above content has been disclosed on the filing date of the present application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0009] The purpose of this application is to provide a water spraying device and method for an aircraft engine water swallowing test to overcome or alleviate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] On the one hand, a water spraying device for an aircraft engine water swallowing test is provided, comprising:

[0012] The support frame is rectangular, hollow at the bottom edge, with a water supply connector at one end and multiple water supply connection holes distributed along its axial direction on the front side wall; the edges of both sides of the support frame are provided with multiple pairs of forward support rod fixing supports distributed along its axial direction;

[0013] Multiple water spray pipes are bent backward at both ends and connected to the top and bottom edges of the support frame with quick-release joints to connect the various water supply connection holes; the side wall of each water spray pipe has multiple pairs of water spray holes distributed along its axial direction and facing the edges of both sides of the support frame; the side wall of each water spray pipe has multiple rear support rod fixing supports distributed along its axial direction, forming multiple rows of rear support rod fixing supports;

[0014] Multiple support poles;

[0015] Multiple pairs of support rod forward fixing clamps are connected to each pair of forward support rod fixing supports with bolts, and cooperate with each pair of forward support rod fixing supports to clamp the two ends of each support rod;

[0016] A plurality of groups of rear support rod fixing clamps are connected to the rear support rod fixing supports of each row with bolts, and cooperate with the rear support rod fixing supports of each row to clamp the side walls of each water spray pipe.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine water swallowing test water spraying equipment, the four edges of the support frame and each water spraying pipe and support rod are made of stainless steel and have a circular cross-section.

[0018] According to at least one embodiment of the present application, in the above-mentioned water spraying equipment for the aircraft engine water swallowing test, the bottom of the edge of both sides of the support frame is provided with supporting legs, and the bottom of the two supporting legs is connected to a pad;

[0019] The aero-engine water swallowing test water spraying equipment further comprises:

[0020] Two support rods, one end of which is connected to the top of the edge of each side of the support frame, and the other end is tilted downward behind the support frame, and the bottom of the end is connected to a pad;

[0021] A crossbeam is connected between the two struts and is located close to the bottom edge of the support frame;

[0022] A support beam is connected between the two support rods and the edges of both sides of the support frame and the support legs.

[0023] Another aspect provides an aircraft engine water ingestion test method, comprising:

[0024] According to the requirements of the water spray particle size, flow rate and distribution of the aircraft engine water swallowing test, a water spray pipe with corresponding water spray hole diameter and distribution position is selected to assemble the above-mentioned aircraft engine water swallowing test water spray equipment;

[0025] Place the water jet equipment for the aircraft engine water swallowing test in front of the aircraft engine, with the support frame placed perpendicular to the aircraft engine axis and no more than 300mm from the aircraft engine inlet;

[0026] Starting aircraft engines;

[0027] Connect the water supply pipe to the water supply joint to supply water. By controlling the water supply pressure, the water holes on the root water spray pipe spray out liquid water that meets the requirements of the water spray particle size, flow rate and distribution of the aircraft engine water swallowing test. The liquid water enters the aircraft engine through the aircraft engine air intake to carry out the water swallowing test. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Schematic diagram of a water spraying device for an aircraft engine water swallowing test provided in an embodiment of the present application;

[0029] Figure 2 This is a schematic diagram of water supply and water spraying of the water spray equipment for the aircraft engine water swallowing test provided in an embodiment of the present application;

[0030] Figure 3 is a schematic diagram of a support frame and its supporting structure provided by an embodiment of the present application;

[0031] Figure 4 is a schematic diagram of a water spray pipe provided in an embodiment of the present application;

[0032] Figure 5 is a schematic cross-sectional view of a water spray pipe provided in an embodiment of the present application;

[0033] Figure 6 This is a schematic diagram of the connection between the support frame and the water spray pipe provided in an embodiment of the present application;

[0034] Figure 7 This is a schematic diagram of the connection between the support frame and the support rods provided in an embodiment of the present application;

[0035] Figure 8 This is a schematic diagram of the connection between the water spray pipe and the support rod provided in an embodiment of the present application;

[0036] in:

[0037] 1-support frame; 2-sprinkler pipe; 3-support rod; 4-forward fixing block of support rod; 5-rearward fixing block of support rod; 6-support leg; 7-support rod; 8-crossbeam; 9-support beam.

[0038] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0039] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0040] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0041] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0042] The following is combined with Figures 1 to 8 This application is described in further detail.

[0043] On the one hand, a water spraying device for an aircraft engine water swallowing test is provided, comprising:

[0044] The support frame 1 is rectangular, hollow at the bottom edge, with a water supply connector at one end and multiple water supply connection holes distributed along its axial direction on the front side wall; the edges of both sides of the support frame 1 have multiple pairs of forward support rod fixing supports distributed along its axial direction;

[0045] Multiple water spray pipes 2 are bent backward at both ends and connected to the top and bottom edges of the support frame 1 with quick-release joints, communicating with various water supply connection holes; the side wall of each water spray pipe 2 has multiple pairs of water spray holes distributed along its axial direction and facing the edges of both sides of the support frame 1; the side wall of each water spray pipe 2 has multiple rearward support rod fixing supports distributed along its axial direction, forming multiple rows of rearward support rod fixing supports;

[0046] Multiple support rods 3;

[0047] Multiple pairs of support rod forward fixing clamps 4 are connected to each pair of forward support rod fixing supports with bolts, and cooperate with each pair of forward support rod fixing supports to clamp the ends of each support rod 3;

[0048] Multiple groups of rear support rod fixing clamps 5 are connected to the rear support rod fixing supports of each row with bolts, and cooperate with the rear support rod fixing supports of each row to clamp the side walls of each water spray pipe 2.

[0049] When conducting a water swallowing test using the water spraying equipment for an aircraft engine water swallowing test disclosed in the above embodiment, water can be supplied by connecting a water supply pipe via a water supply connector. Water enters each water spray pipe 2 through the bottom edge of the support frame 1 and is then sprayed out through the water spray holes on each water spray pipe 2. Depending on the requirements of the water spray particle size, flow rate, and distribution in the aircraft engine water swallowing test, water spray pipes 2 with corresponding water spray hole diameters and distribution positions can be selected, and the corresponding water spray particle size, flow rate, and distribution can be generated in accordance with the water supply pressure.

[0050] As for the water spraying equipment for the aircraft engine water swallowing test disclosed in the above embodiment, those skilled in the art will understand that its design utilizes multiple water spray holes on multiple water spray pipes 2 arranged in parallel to spray water. The overall structure is simple, and the water supply is uniform. The water spray particle size, flow rate and distribution can be adjusted by replacing the water spray pipes 2 with different water spray hole diameters and distribution positions, which is convenient and quick.

[0051] As for the water spraying equipment for the aircraft engine water swallowing test disclosed in the above embodiment, those skilled in the art will understand that, during the water swallowing test, the entire equipment can be placed in front of the aircraft engine, with the support frame 1 arranged perpendicular to the axis of the aircraft engine. Since the water spraying holes on the side walls of each water spraying pipe 2 face the edges on both sides of the support frame 1, the sprayed water is perpendicular to the air intake direction of the aircraft engine and is sucked into the aircraft engine by the air intake of the aircraft engine, which can greatly eliminate the influence of the axial velocity of the water spray on the test.

[0052] As for the water spraying equipment for the water swallowing test of an aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the two ends of each water spraying pipe 2 are bent backwards and connected to the top and bottom edges of the support frame 1 with quick-release joints, and the support frame 1, the water spraying pipe 2 and the support rod 3 are fixed by means of front and rear cooperating fixed supports and fixed clamps. The overall structure is compact, the fixation is reliable, and it is easy to assemble and disassemble. A slot can be formed between the fixed supports and the fixed clamps to clamp the support rod 3.

[0053] In some optional embodiments, in the above-mentioned aircraft engine water swallowing test water spraying equipment, the four edges of the support frame 1 and each water spraying pipe 2 and support rod 3 are made of stainless steel and have a circular cross-section, so as to effectively reduce the disturbance of the water spraying equipment to the aircraft engine intake. During the test, the equipment can be arranged close to the aircraft engine inlet to avoid distortion of the aircraft engine intake, and to avoid the sprayed liquid water being affected by the aircraft engine intake air flow field, showing a central contraction trend, and concentrating in the center of the aircraft engine, and almost all of it will be sucked into the interior of the aircraft engine, thereby avoiding excessive testing.

[0054] In some optional embodiments, in the above-mentioned water spraying equipment for the aircraft engine water swallowing test, the bottom of the edge of both sides of the support frame 1 is provided with support legs 6, and the bottom of the two support legs 6 is connected to a pad, which can be connected to the base for fixation;

[0055] The aero-engine water swallowing test water spraying equipment further comprises:

[0056] Two support rods 7, one end of which is connected to the top of the edge of both sides of the support frame 1, and the other end is inclined downward behind the support frame 1, and the bottom of the end is connected to a pad, which can be connected to the base for fixing, thereby obliquely supporting the support frame 1;

[0057] A crossbeam 8 is connected between the two support rods 7 and is close to the bottom edge of the support frame 1 to enhance the reliability of the support frame 1;

[0058] A support beam 9 is connected between the two support rods 7 and the edges of the support frame 1 and its legs 6, so that a triangular stable support can be constructed between the two support rods 7 and the edges of the support frame 1 and its legs 6;

[0059] The legs 6, the struts 7, the cross beams 8 and the support beams 9 are made of stainless steel and have a circular cross section.

[0060] Another aspect provides an aircraft engine water ingestion test method, comprising:

[0061] According to the requirements of the water spray particle size, flow rate and distribution of the aircraft engine water swallowing test, a water spray pipe 2 with corresponding water spray hole diameter and distribution position is selected to assemble the above-mentioned aircraft engine water swallowing test water spray equipment;

[0062] The water jet equipment for the aircraft engine water swallowing test is placed in front of the aircraft engine, wherein the support frame 1 is placed perpendicular to the axis of the aircraft engine and is no more than 300 mm away from the aircraft engine inlet;

[0063] Starting aircraft engines;

[0064] Connect the water supply pipe to the water supply joint to supply water. By controlling the water supply pressure, the water spray hole on the root water spray pipe 2 sprays out liquid water that meets the requirements of the water spray particle size, flow rate and distribution of the aircraft engine water swallowing test. The liquid water enters the aircraft engine through the aircraft engine air intake to carry out the water swallowing test.

[0065] The aircraft engine water swallowing test method disclosed in the above embodiment is implemented based on the aircraft engine water swallowing test water spraying equipment disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the aircraft engine water swallowing test water spraying equipment part. Its technical effects can also refer to the technical effects of the relevant part of the method, which will not be repeated here.

[0066] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0067] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A water spraying device for an aircraft engine water swallowing test, characterized in that: include: The support frame (1) is rectangular, with a hollow bottom edge, a water supply connector at one end, and a plurality of water supply connection holes distributed along the axial direction of the side wall; the edges of both sides of the support frame (1) are provided with a plurality of pairs of forward support rod fixing supports distributed along the axial direction; A plurality of water spray pipes (2) are bent backward at both ends and connected to the top edge and the bottom edge of the support frame (1) with quick-release joints, and are connected to the various water supply connection holes; the side wall of each water spray pipe (2) has a plurality of pairs of water spray holes distributed along its axial direction and facing the edges of both sides of the support frame (1); the water sprayed from each water spray hole is perpendicular to the air intake direction of the aircraft engine and is sucked into the aircraft engine by the aircraft engine air intake; the side wall of each water spray pipe (2) has a plurality of rear support rod fixing supports distributed along its axial direction, forming a plurality of rows of rear support rod fixing supports; multiple support rods (3); Multiple pairs of support rod forward fixing clamps (4) are connected to each pair of forward support rod fixing supports with bolts, and cooperate with each pair of forward support rod fixing supports to clamp both ends of each support rod (3); Multiple groups of rear support rod fixing clamps (5) are connected to the rear support rod fixing supports of each row with bolts, and cooperate with the rear support rod fixing supports of each row to clamp the side walls of each water spray pipe (2); The four edges of the support frame (1) and each water spray pipe (2) and support rod (3) are made of stainless steel and have a circular cross section. The support frame (1) is placed perpendicular to the axis of the aircraft engine and is no more than 300 mm away from the aircraft engine inlet.

2. The water spraying equipment for the aircraft engine water swallowing test according to claim 1, characterized in that: The bottom of the two side edges of the support frame (1) are provided with supporting legs (6), and the bottoms of the two supporting legs (6) are connected to pads; The aero-engine water swallowing test water spraying equipment further comprises: Two support rods (7), one end of which is connected to the top of the edge of both sides of the support frame (1), and the other end of which is tilted downward behind the support frame (1), and the bottom of which is connected to a pad; A crossbeam (8) is connected between the two support rods (7), and the crossbeam (8) is close to the bottom edge of the support frame (1); A support beam (9) is connected between the two support rods (7) and the edges of both sides of the support frame (1) and its legs (6).

3. A method for testing an aircraft engine for water swallowing, implemented based on the water spraying device for the aircraft engine for water swallowing test disclosed in claim 2, characterized in that: include: According to the requirements of the water spray particle size, flow rate and distribution of the aircraft engine water swallowing test, a water spray pipe (2) with a corresponding water spray hole diameter and distribution position is selected to assemble the aircraft engine water swallowing test water spray equipment as described in claim 2; The water jet device for the aircraft engine water swallowing test is placed in front of the aircraft engine, wherein the support frame (1) is placed perpendicular to the axis of the aircraft engine and is not more than 300 mm away from the aircraft engine inlet; Starting aircraft engines; The water supply pipe is connected to the water supply joint to supply water. By controlling the water supply pressure, the water spray hole on the root water spray pipe (2) sprays out liquid water that meets the requirements of the water spray particle size, flow rate and distribution of the aircraft engine water swallowing test. The liquid water enters the aircraft engine through the aircraft engine intake to perform the water swallowing test.

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