A kind of aircraft engine air system test sensor installation modeling tool and method

Abstract

The present application belongs to the technical field of installation and shaping of aircraft engine air system test sensors, and specifically relates to an installation and shaping tool and method for aircraft engine air system test sensors, wherein the measuring end lifting shaping hole on the support plate is used to process the measuring end of the sensor to lift the measuring end, and the lifting height can be controlled by the depth of the sensor measuring end inserted into the measuring end lifting shaping hole, and the lifting angle can be controlled by designing the angle between the measuring end lifting shaping hole and the edge of the support plate, and the semicircular shaping notch of the lead on the support plate and its slider and semicircular shaping column of the lead are used to process the semicircular shape of the sensor lead, and the shape of the semicircle can be controlled by designing the diameter of the semicircular shaping column and the gap between the semicircular shaping notch and the lead, so that the shaping of the sensor can be completed conveniently and quickly, and it is easy to remove.

Description

Technical Field

[0001] The present application belongs to the technical field of installation and shaping of test sensors for aircraft engine air systems, and specifically relates to a tool and method for installation and shaping of test sensors for aircraft engine air systems. Background Art

[0002] The test of aircraft engine air system involves the measurement of cavity pressure and cavity temperature, which are mostly measured by temperature and pressure sensors, such as armored thermocouples and pressure measuring tubes.

[0003] Currently, sensors used to measure the cavity pressure and temperature of aircraft engine air systems are mostly installed using a tilting installation process. During installation, the sensor measuring end and its lead are manually shaped using flat-nose pliers to tilt the sensor measuring end, and a semicircle is machined on the sensor lead. The sensor lead is then fixed to the inner wall of the air system with a spot-welded metal sheet, and measurement is performed through a measurement lead opened on the side wall of the air system. This technical solution has the following drawbacks:

[0004] 1) Manual shaping of the sensor measuring end using flat-nose pliers resulted in deviations in the height and angle of the sensor measuring end from standard requirements, resulting in poor accuracy and consistency in the measurement data during aircraft engine air system testing.

[0005] 2) Manual shaping of the sensor lead using flat-nose pliers resulted in a semicircular shape that deviated from standard requirements, affecting the sensor's installation and positioning on the inner wall of the air system. This, in turn, affected the height and angle of the sensor's measuring end when mounted on the inner wall of the air system, resulting in poor measurement data accuracy and consistency during aircraft engine air system testing.

[0006] 3) Manual shaping of the sensor measuring end and its leads using flat-nose pliers requires repeated bending and adjustment, which is inefficient and can easily damage the sensor.

[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 this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0009] The purpose of this application is to provide an aircraft engine air system test sensor installation modeling tool and method to overcome or alleviate at least one of the existing technical defects.

[0010] The technical solution of this application is:

[0011] On the one hand, a tool for installing a test sensor for an aircraft engine air system is provided, comprising:

[0012] The support plate has a measuring end tilting shape hole and a lead semicircular shape notch on its edge, and a support protrusion on the side wall; the support protrusion has a guide groove perpendicular to the support plate;

[0013] A slider is connected to the guide groove via a guide rail and has a slider connection hole;

[0014] The slider adjustment screw is screwed on the support plate and partially extends into the slider connection hole, and the side wall of the portion has a slider connection groove;

[0015] The slider fixing screw is screwed on the slider and partially extends into the slider connection groove; turning the slider adjustment screw can drive the slider to slide in the guide groove;

[0016] The hinged rod has one end hinged to the support plate through a single-double-ear structure using a pin and its nut, and the other end has a molding column connection hole on the side wall;

[0017] Lead the semicircular molding column, one end of which is inserted into the molding column connection hole;

[0018] The molding column fixing top screw is screwed on the hinge rod and abuts against the side wall of one end of the lead semicircular molding column inserted into the molding column connection hole;

[0019] Toggling the hinged rod can drive the other end of the lead semicircular modeling column to be stuck in or out of the lead semicircular modeling notch. When this end of the lead semicircular modeling column is stuck in the lead semicircular modeling notch, there is a gap between it and the lead semicircular modeling notch.

[0020] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air system test sensor installation molding tooling, there are three measuring end tilting molding holes on the edge of the support plate, and the angles between the three measuring end tilting molding holes and the edge of the support plate are 30°, 45°, and 60°, and there is a smooth transition between the three measuring end tilting molding holes and the edge of the support plate.

[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air system test sensor installation molding tool, the two side walls of the semicircular molding notch of the lead are arc-shaped.

[0022] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air system test sensor installation molding tooling, there are two support protrusions on the support plate and their corresponding sliders, slider adjustment screws, and slider fixing top screws, which are distributed on both sides of the semicircular molding notch of the lead on the support plate.

[0023] According to at least one embodiment of the present application, in the aforementioned aircraft engine air system test sensor installation molding tool, the bottom wall of the semicircular molding notch of the lead wire has a positioning protrusion;

[0024] The semicircular modeling column can be stuck in the semicircular modeling notch of the lead wire and has a positioning opening on the end surface. When the end of the semicircular modeling column is stuck in the semicircular modeling notch of the lead wire, the positioning opening is stuck on the positioning protrusion.

[0025] Another aspect provides a method for installing and molding an aircraft engine air system test sensor, comprising:

[0026] Insert the measuring end of the sensor into the tilting hole on the support plate and bend it to tilt the measuring end of the sensor.

[0027] Turn the slider adjustment screw to drive the slider to slide, so that the slider and the support plate cooperate to clamp the sensor lead;

[0028] Move the hinged rod to make the corresponding end of the semicircular lead column come out of the semicircular lead notch on the support plate;

[0029] Bend the sensor lead 90° inward along the semicircular notch on the support plate, close to the protruding side wall of the support, and cross it through the semicircular notch.

[0030] Move the hinged rod to make the semicircular lead column snap into the semicircular lead notch on the support plate;

[0031] Bend the sensor lead wire 180° around the semicircular lead wire column and pass it back across the semicircular lead wire notch.

[0032] Bend the sensor lead 90° outward along the semicircular notch of the lead on the support plate away from the protruding side wall of the support, completing the semicircular processing on the sensor lead;

[0033] Turn the slider adjustment screw to drive the slider to slide away from the support plate and loosen the sensor lead;

[0034] Move the hinged rod to make the corresponding end of the lead semicircular shape column fall out of the lead semicircular shape notch on the support plate, and remove the sensor from the aircraft engine air system test sensor installation tooling.

[0035] This application has at least the following beneficial technical effects:

[0036] Provided is an aircraft engine air system test sensor installation shaping tool, which uses a measuring end tilting shaping hole on a support plate to make the measuring end of the sensor tilted, and the tilting height can be controlled by the depth of the sensor measuring end inserted into the measuring end tilting shaping hole, and the tilting angle can be controlled by designing the angle between the measuring end tilting shaping hole and the edge of the support plate, and uses a semicircular shaping notch of a lead wire and its slider and a semicircular shaping column on the support plate to process a semicircular portion of the sensor lead wire, and the shape of the semicircle can be controlled by designing the diameter of the semicircular shaping column and the gap between the semicircular shaping column and the semicircular shaping notch of the lead wire. The shaping of the sensor can be completed conveniently and quickly, and is easy to remove, so that the shaping of the sensor meets standard requirements, ensures the reliability of the sensor's installation and positioning on the inner wall of the air system, and ensures the accuracy and consistency of the measurement data, avoids repeated bending and adjustment of the sensor, has high efficiency, and avoids damage to the sensor. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 This is a schematic diagram of the current tilt-up installation process for installing the sensor on the inner wall of the air system;

[0038] Figure 2 Schematic diagram of an aircraft engine air system test sensor installation tool provided in an embodiment of the present application;

[0039] Figure 3 is a schematic diagram of a support plate provided in an embodiment of the present application;

[0040] Figure 4 is a schematic diagram of a slider provided in an embodiment of the present application;

[0041] Figure 5 Schematic diagram of a slider adjustment screw provided in an embodiment of the present application;

[0042] Figure 6 Schematic diagram of a slider fixing screw provided in an embodiment of the present application;

[0043] Figure 7 is a schematic diagram of a hinged rod provided in an embodiment of the present application;

[0044] Figure 8 Schematic diagram of a semicircular lead column provided in an embodiment of the present application;

[0045] Figure 9 Schematic diagram of fixing the top screw of the molding column provided in an embodiment of the present application;

[0046] Figure 10-13 This is a schematic diagram of the installation and shaping process of an aircraft engine air system test sensor provided in an embodiment of the present application;

[0047] in:

[0048] 1-Support plate; 2-Slider; 3-Slider adjustment screw; 4-Slider fixing screw; 5-Hinged rod; 6-Lead semicircular molding column; 7-Mouldation column fixing screw; 8-Sensor.

[0049] 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 limitations on this patent. DETAILED DESCRIPTION

[0050] 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.

[0051] 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.

[0052] 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.

[0053] The following is combined with Figures 1 to 13 This application is described in further detail.

[0054] On the one hand, a tool for installing a test sensor for an aircraft engine air system is provided, comprising:

[0055] The support plate 1 has a measuring end tilting shape hole and a lead semicircular shape notch on its edge, and a supporting protrusion on the side wall; the supporting protrusion has a guide groove perpendicular to the support plate 1;

[0056] Slider 2 is connected to the guide groove through the guide rail and has a slider connection hole;

[0057] The slider adjustment screw 3 is screwed on the support plate 1 and partially extends into the slider connection hole. The side wall of this part has a slider connection groove;

[0058] The slider fixing screw 4 is screwed on the slider 2 and partially extends into the slider connection groove; turning the slider adjustment screw 3 can drive the slider 2 to slide in the guide groove;

[0059] The hinge rod 5 has one end hinged to the support plate 1 by a pin and its nut through a single-double-ear structure, and the other end has a molding column connection hole on the side wall;

[0060] One end of the semicircular molding column 6 is inserted into the molding column connection hole;

[0061] The molding column fixing screw 7 is screwed on the hinge rod 5 and abuts against the side wall of one end of the lead semicircular molding column 6 inserted into the molding column connection hole;

[0062] Toggling the hinged rod 5 can drive the other end of the lead semicircular modeling column 6 to be stuck in or out of the lead semicircular modeling notch. When this end of the lead semicircular modeling column 6 is stuck in the lead semicircular modeling notch, there is a gap between it and the lead semicircular modeling notch.

[0063] The above-mentioned embodiment discloses an aircraft engine air system test sensor installation shaping tool, which can use the measuring end tilting shaping hole on the support plate 1 to process the measuring end of the sensor 8 to tilt the measuring end. The tilting height can be controlled by the depth of the measuring end of the sensor 8 inserted into the measuring end tilting shaping hole. The tilting angle can be controlled by designing the angle between the measuring end tilting shaping hole and the edge of the support plate 1, and the lead semicircular shaping notch on the support plate 1 and its slider 2, the lead semicircular shaping column 6 are used to process the upper semicircle of the lead of the sensor 8. The shape of the semicircle can be controlled by designing the diameter of the lead semicircular shaping column 6 and the gap between the lead semicircular shaping notch. The shaping of the sensor 8 can be completed conveniently and quickly, and it is easy to remove, so that the shaping of the sensor 8 meets the standard requirements, ensures the reliability of the installation and positioning of the sensor 8 on the inner wall of the air system, and ensures the accuracy and consistency of the measurement data. It can avoid repeated bending and adjustment of the sensor 8, has high efficiency, and avoids damage to the sensor 8. The process of shaping the sensor 8, the specific process can be referred to the aircraft engine air system test sensor installation shaping method disclosed in the embodiment of the present application.

[0064] As for the aircraft engine air system test sensor installation molding tool disclosed in the above embodiment, technical personnel in the field can understand that its design uses the slider fixing top screw 4 to connect the slider adjustment screw 3 and the slider 2, and uses the molding column fixing top screw 7 to connect the hinge rod 5 and the lead semicircular molding column 6, so that the slider adjustment screw 3 and the lead semicircular molding column 6 can be quickly replaced when they are damaged.

[0065] In some optional embodiments, in the above-mentioned aircraft engine air system test sensor installation molding tooling, there are three measuring end tilting molding holes on the edge of the support plate 1, and the angles between the three measuring end tilting molding holes and the edge of the support plate 1 are 30°, 45°, and 60°, and there is a smooth transition between the three measuring end tilting molding holes and the edge of the support plate 1. When the measuring end of the sensor 8 is tilted, the measuring end of the sensor 8 can be inserted into the measuring end tilting molding hole with a corresponding angle between the three measuring end tilting holes and the edge of the support plate 1 for bending according to the required tilting angle.

[0066] In some optional embodiments, in the above-mentioned aircraft engine air system test sensor installation molding tool, the two side walls of the semicircular molding notch of the lead are arc-shaped.

[0067] In some optional embodiments, in the above-mentioned aircraft engine air system test sensor installation molding tooling, there are two supporting protrusions on the support plate 1 and their corresponding sliders 2, slider adjustment screws 3, and slider fixing top screws 4, which are distributed on both sides of the semicircular molding notch of the lead on the support plate 1.

[0068] In some optional embodiments, in the above-mentioned aircraft engine air system test sensor installation molding tool, the bottom wall of the semicircular molding notch of the lead wire has a positioning protrusion;

[0069] The semicircular shaping column 6 can be stuck into the end face of one end of the semicircular shaping notch of the lead wire and has a positioning opening. When this end of the semicircular shaping column 6 is stuck into the semicircular shaping notch of the lead wire, the positioning opening is stuck on the positioning protrusion, thereby preventing the semicircular shaping column 6 from shaking sideways in the semicircular shaping notch of the lead wire.

[0070] Another aspect provides a method for installing and molding an aircraft engine air system test sensor, comprising:

[0071] Insert the measuring end of the sensor 8 into the measuring end tilting hole on the support plate 1 and bend it so that the measuring end of the sensor 8 tilts up;

[0072] Place the sensor 8 lead wire into the guide groove, turn the slider adjustment screw 3 to drive the slider 2 to slide, so that the slider 2 and the support plate 1 cooperate to clamp the sensor 8 lead wire;

[0073] Move the hinge rod 5 to make the corresponding end of the semicircular lead column 6 come out of the semicircular lead notch on the support plate 1;

[0074] Bend the sensor 8 lead wire 90 degrees inward along the semicircular notch of the lead wire on the support plate 1 close to the side wall of the support protrusion, and cross it through the semicircular notch of the lead wire. Figure 10 As shown;

[0075] Move the hinge rod 5 to make the semicircular lead column 6 snap into the semicircular lead notch on the support plate 1;

[0076] Bend the sensor 8 lead wire 180° around the semicircular lead wire column 6 and pass it back through the semicircular lead wire notch. Figure 11 As shown;

[0077] Bend the sensor 8 lead wire 90 degrees outward along the semicircular notch of the lead wire on the support plate 1 away from the side wall of the support protrusion, and complete the semicircular processing on the sensor 8 lead wire. Figure 12 As shown;

[0078] Turn the slider adjustment screw 3 to drive the slider 2 to slide away from the support plate 1 and loosen the lead wire of the sensor 8;

[0079] Move the hinge rod 5 to make the corresponding end of the semicircular lead column 6 come out of the semicircular lead notch on the support plate 1. Figure 13 As shown, the sensor 8 is removed from the aircraft engine air system test sensor installation molding tool.

[0080] The aircraft engine air system test sensor installation molding tooling disclosed in the above embodiment is implemented based on the aircraft engine air system test sensor installation molding tooling disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant instructions of the aircraft engine air system test sensor installation molding tooling part. Its technical effects can also refer to the technical effects of the relevant parts of the aircraft engine air system test sensor installation molding tooling, which will not be repeated here.

[0081] 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.

[0082] 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. An aircraft engine air system test sensor installation molding tool, characterized in that: include: A support plate (1) having a measuring end tilting shape hole and a lead semicircular shape notch on its edge, and a support protrusion on its side wall; the support protrusion has a guide groove perpendicular to the support plate (1); A slider (2) is connected to the guide groove via a guide rail and has a slider connection hole; A slider adjustment screw (3) is screwed onto the support plate (1), partially extending into the slider connection hole, and a side wall of the portion has a slider connection groove; The slider fixing screw (4) is screwed onto the slider (2) and partially extends into the slider connection groove; turning the slider adjustment screw (3) can drive the slider (2) to slide in the guide groove; A hinged rod (5) has one end hinged to the support plate (1) through a single-double-ear structure using a pin and its nut, and a side wall of the other end has a molding column connection hole; A semicircular molding column (6) is inserted at one end into the molding column connection hole; The molding column fixing top screw (7) is screwed on the hinge rod (5) and abuts against the side wall of one end of the lead semicircular molding column (6) inserted into the molding column connection hole; The hinged rod (5) can be moved to drive the other end of the lead semicircular shape column (6) to be stuck in or out of the lead semicircular shape notch. When the end of the lead semicircular shape column (6) is stuck in the lead semicircular shape notch, a gap exists between the end and the lead semicircular shape notch. The measuring end tilting shaping hole has an included angle with the edge of the support plate (1), and has a smooth transition with the edge of the support plate (1). When the measuring end of the sensor (8) is tilted, the measuring end of the sensor (8) is inserted into the measuring end tilting shaping hole having a corresponding included angle with the edge of the support plate (1) and bent.

2. The aircraft engine air system test sensor installation molding tool according to claim 1 is characterized in that: The edge of the support plate (1) is provided with three measuring end tilting shaping holes, and the angles between the three measuring end tilting shaping holes and the edge of the support plate (1) are 30°, 45°, and 60°.

3. The aircraft engine air system test sensor installation molding tool according to claim 2 is characterized in that: The walls on both sides of the semicircular notch of the lead are arc-shaped.

4. The aircraft engine air system test sensor installation molding tool according to claim 3 is characterized in that: There are two support protrusions on the support plate (1) and their corresponding sliders (2), slider adjustment screws (3), and slider fixing top screws (4), which are distributed on both sides of the semicircular shape notch of the lead on the support plate (1).

5. The aircraft engine air system test sensor installation molding tool according to claim 4 is characterized in that: The bottom wall of the semicircular notch of the lead has a positioning protrusion; The semicircular molding column (6) is capable of being clamped into the semicircular molding notch of the lead wire and has a positioning opening on its end surface. When the end of the semicircular molding column (6) is clamped into the semicircular molding notch of the lead wire, the positioning opening is clamped on the positioning protrusion.

6. A method for installing and shaping an aircraft engine air system test sensor, based on the aircraft engine air system test sensor installation and shaping tooling according to claim 5, characterized in that: include: Insert the measuring end of the sensor (8) into the measuring end tilting hole on the support plate (1), and bend it so that the measuring end of the sensor (8) tilts up; Twist the slider adjustment screw (3) to drive the slider (2) to slide, so that the slider (2) and the support plate (1) cooperate to clamp the sensor (8) lead; Move the hinge rod (5) to make the corresponding end of the lead semicircular shape column (6) fall out of the lead semicircular shape notch on the support plate (1); Bend the sensor (8) lead wire 90° inward along the semicircular notch of the lead wire on the support plate (1) close to the side wall of the support protrusion, and cross it through the semicircular notch of the lead wire; Move the hinge rod (5) to make the semicircular lead column (6) snap into the semicircular lead notch on the support plate (1); Bend the sensor (8) lead wire 180° around the lead wire semicircular molding column (6) and pass it back across the lead wire semicircular molding notch; Bend the sensor (8) lead wire outwards by 90° along the semicircular notch of the lead wire on the support plate (1) away from the protruding side wall of the support, and complete the semicircular processing on the sensor (8) lead wire; Twist the slider adjustment screw (3) to drive the slider (2) to slide, so that the slider (2) is away from the support plate (1), and the sensor (8) lead is loosened; The hinge rod (5) is moved to make the corresponding end of the lead semicircular molding column (6) come out of the lead semicircular molding notch on the support plate (1), and the sensor (8) is removed from the aircraft engine air system test sensor installation molding tool.

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