Pipeline air entraining structure of aero-engine spanning inner and outer casings and assembling method of pipeline air entraining structure

Abstract

The invention belongs to the technical field of aero-engine air entraining design, and particularly relates to a pipeline air entraining structure of an aero-engine spanning an inner casing and an outer casing and an assembling method.The pipeline air entraining structure of the aero-engine spanning the inner casing and the outer casing comprises an inner air entraining pipeline arranged between the inner casing and the outer casing, the outer wall of the outlet end of the inner-layer casing is in a spherical shape; one end of the reducing sleeve is an inner side end, the other end of the reducing sleeve is an outer side end, the inner wall of the inner side end of the reducing sleeve is spherical, and the reducing sleeve is connected to the outlet end of the inner air entraining pipeline in a sleeving mode; the outer wall of the outer side end of the reducing sleeve is spherical and extends out of an outer air leading hole formed in the outer casing; the inlet end of the outer gas leading pipeline is connected to the outer casing, the inner wall of the outer gas leading pipeline is cylindrical, and the outer gas leading pipeline is arranged at the outer side end of the reducing sleeve in a sleeving mode.

Description

Technical Field

[0001] The present application belongs to the technical field of aero-engine air bleed design, and specifically relates to a pipeline air bleed structure and an assembly method for an aero-engine spanning inner and outer casings. Background Art

[0002] The cooling and temperature equalization of high-temperature components of aircraft engines, the sealing and insulation of internal disc cavities and bearing lubrication systems, and the adjustment of rotor axial forces require the use of pipelines to bleed air from the internal flow channels of aircraft engines.

[0003] With the development of technology, the amount of bleed air required for cooling and temperature equalization of high-temperature components of aircraft engines, sealing and insulation of internal disc cavities and bearing lubrication systems, and adjustment of rotor axial force is increasing. Correspondingly, pipelines are used to bleed air from the internal flow channels of aircraft engines. The diameter of the required pipelines is increasing, and the rigidity is increasing. The pipelines cross the inner and outer casings of aircraft engines to bleed air, which will be subjected to greater stress caused by the uncoordinated deformation of the inner and outer casings, and are very prone to breakage, seriously affecting the safety of aircraft engine operation. This problem becomes increasingly prominent with the increase in bleed air temperature.

[0004] In order to reduce the stress on the air duct caused by the uncoordinated deformation of the inner and outer casings of aircraft engines, the following methods are currently used: Figure 1 The structural compensation scheme shown is that the inner air duct is arranged between the inner casing and the outer casing, and the inlet end of the inner air duct is connected to the inner casing and communicated with the inner air hole opened on the inner casing; the outlet end of the inner air duct is connected to the pipe joint, the pipe joint extends from the outer air hole opened on the outer casing, and is connected to the inlet end of the outer air pipe, the outer wall of the pipe joint has an annular groove, and a sealing plug is sleeved on the outer periphery of the pipe joint; the sealing plug is connected to the outer casing, and a sealing ring is arranged inside the through hole thereof; the outer ring of the sealing ring is in sealing contact with the through hole on the sealing plug, and the inner ring is stuck in the annular groove, and there is a gap between the inner ring and the bottom of the annular groove.

[0005] In such Figure 1 In the technical solution shown, the high-pressure gas in the inner casing can be led out through the inner bleed air pipeline and the outer bleed air pipeline to provide cooling and temperature equalization for the high-temperature components of the aircraft engine, sealing and heat insulation of the internal disc cavity and the bearing lubrication system, and adjustment of the axial force of the rotor. The sealing ring can slide along the through hole of the sealing plug cover and the sealing ring can move in the annular groove on the pipe joint to release the radial, circumferential and circumferential stresses caused by the uncoordinated deformation of the inner and outer casings, thereby avoiding the rupture of the pipeline. This technical solution has the following defects:

[0006] 1) The inner air bleed pipe and the outer air bleed pipe are rigidly connected. The inner air bleed pipe needs to be fixed on the inner casing, and the outer air bleed pipe needs to be fixed on the outer casing. They require high processing and positioning accuracy for assembly, which makes assembly difficult and easily generates large assembly stress. In addition, when the inner air bleed pipe and the outer air bleed pipe are too strong, there is a risk of thermal deformation inconsistency between the pipe and the casing, which generates harmful stress and reduces the reliability of the structure.

[0007] 2) Structural compensation is performed using the relevant design of the sealing ring. The sealing ring cannot form an assembly with other parts and can only be managed as a loose component, stored and assembled separately, resulting in poor structural maintainability.

[0008] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0009] The purpose of the present application is to provide a pipeline air bleed structure and an assembly method for an aircraft engine that spans the inner and outer casings, so as to overcome or alleviate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] On the other hand, a pipeline air bleed structure for an aircraft engine spanning inner and outer casings is provided, comprising:

[0012] The inner bleed air pipeline is arranged between the inner casing and the outer casing, the inlet end of which is connected to the inner casing and communicated with the inner bleed air hole provided on the inner casing, and the outer wall of the outlet end thereof is spherical;

[0013] The adapter sleeve has one end as the inner end and the other end as the outer end, wherein the inner wall of the adapter sleeve is spherical and is sleeved on the outlet end of the inner air duct; the outer wall of the adapter sleeve is spherical. Extending from the external air bleed hole provided on the outer casing;

[0014] The inlet end of the external air bleed pipeline is connected to the outer casing, and the inner wall is cylindrical and is sleeved on the outer end of the adapter sleeve.

[0015] According to at least one embodiment of the present application, in the above-mentioned air bleed pipe structure spanning the inner and outer casings of the aircraft engine, a small gap is fitted between the outlet end of the inner bleed pipe and the inner end of the adapter sleeve;

[0016] There is a small gap between the inlet end of the external air pipeline and the outer end of the adapter sleeve.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine air bleed structure spanning the inner and outer casings, the inner wall of the inlet end of the external air bleed pipe has an annular limiting protrusion, and the annular limiting protrusion has a smooth transition bevel between the inner wall of the inlet end of the external air bleed pipe on one side facing the adapter sleeve.

[0018] According to at least one embodiment of the present application, in the above-mentioned pipeline air bleed structure of the aircraft engine spanning the inner and outer casings, the outer wall of the inlet end of the inner air bleed pipeline has an annular connecting edge, and the annular connecting edge is connected to the annular boss surrounding the inner air bleed hole on the inner casing;

[0019] The outer wall of the inlet end of the external air bleed pipeline is provided with an annular connecting edge, and the annular connecting edge is connected to an annular boss surrounding the external air bleed hole on the outer casing.

[0020] On the other hand, a method for assembling a pipeline air bleed structure of an aircraft engine spanning inner and outer casings is provided, which is used to assemble the pipeline air bleed structure of the aircraft engine spanning inner and outer casings, and is characterized by comprising:

[0021] Assemble the internal air bleed pipe and the adapter sleeve, and press the outlet end of the internal air bleed pipe into the inner end of the adapter sleeve through pre-cooling and pre-deformation to form an assembly;

[0022] Assemble the inner bleed air pipeline with the inner casing, connect the inlet end of the inner bleed air pipeline to the inner casing, and communicate with the inner bleed air hole opened on the inner casing;

[0023] Assemble the outer casing and the inner casing, put the outer casing on the outer periphery of the inner casing, and adjust the inner end of the adapter sleeve so that it extends out from the outer air bleed hole provided on the outer casing;

[0024] Assemble the external bleed air pipeline with the outer casing, connect the inlet end of the bleed air pipeline to the outer casing, and adjust so that the inlet end of the bleed air pipeline is sleeved on the outer end of the adapter sleeve.

[0025] This application has at least the following beneficial technical effects:

[0026] Provided are a pipeline air bleed structure spanning inner and outer casings of an aircraft engine and an assembly method thereof. An inner air bleed pipeline and an outer air bleed pipeline are designed to be connected by using an adapter sleeve. The outlet end of the inner air bleed pipeline and the inner side end of the adapter sleeve are in spherical fit contact and can rotate relatively. The inlet end of the outer air bleed pipeline and the outer side end of the adapter sleeve are in cylindrical and spherical fit contact and can rotate and slide relatively. In this way, when the inner air bleed pipeline is fixed to the inner casing and the outer air bleed pipeline is fixed to the outer casing, the stress generated by the uncoordinated deformation of the inner casing and the outer casing can be released with multiple degrees of freedom, and compensation can be performed during structural assembly, thereby reducing the requirements for parts processing and positioning accuracy. In addition, the risk of uncoordinated thermal deformation between the pipeline and the casing can be avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the existing method of using a pipeline to bleed air from the internal flow channel of an aircraft engine;

[0028] Figure 2It is a schematic diagram of a pipeline air bleed structure of an aircraft engine spanning inner and outer casings provided in an embodiment of the present application;

[0029] Figure 3 is a schematic diagram of an internal air bleed pipeline provided in an embodiment of the present application;

[0030] Figure 4 is a schematic diagram of an adapter sleeve provided in an embodiment of the present application;

[0031] Figure 5 is a schematic diagram of an external air bleed pipeline provided in an embodiment of the present application;

[0032] Figure 6 It is a schematic diagram of the air bleed structure compensation of the pipeline across the inner and outer casings of the aircraft engine provided by the embodiment of the present application;

[0033] in:

[0034] 1- internal air bleed pipe; 2- inner casing; 3- outer casing; 4- adapter sleeve; 5- external air bleed pipe.

[0035] In order to better illustrate the present 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 construed as limitations on the present application. DETAILED DESCRIPTION

[0036] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience 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.

[0037] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0038] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" 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 or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0039] A pipeline air bleed structure for an aircraft engine spanning inner and outer casings, such as Figure 2-6 As shown, including:

[0040] The inner air bleed pipe 1 is arranged between the inner casing 2 and the outer casing 3, the inlet end of which is connected to the inner casing 2 and communicated with the inner air bleed hole provided on the inner casing 2, and the outer wall of the outlet end thereof is spherical;

[0041] The adapter sleeve 4 has one end as the inner end and the other end as the outer end, wherein the inner wall of the inner end of the adapter sleeve 4 is spherical and sleeved on the outlet end of the inner bleed air pipeline 1; the outer wall of the outer end of the adapter sleeve 4 is spherical and extends from the outer bleed air hole opened on the outer casing 3;

[0042] The inlet end of the external air bleed pipeline 5 is connected to the outer casing 3 , and the inner wall is cylindrical and is sleeved on the outer end of the adapter sleeve 4 .

[0043] In the air bleed pipe structure of the aircraft engine spanning the inner and outer casings disclosed in the above-mentioned embodiment, the inner air bleed pipe 1 and the outer air bleed pipe 5 are designed to be connected by using an adapter sleeve 4. The outlet end of the inner air bleed pipe 1 and the inner end of the adapter sleeve 4 are in spherical fitting contact and can rotate relatively. The inlet end of the outer air bleed pipe 5 and the outer end of the adapter sleeve 4 are in cylindrical and spherical fitting contact and can rotate and slide relatively. In this way, when the inner air bleed pipe 1 is fixed to the inner casing 2 and the outer air bleed pipe 5 is fixed to the outer casing 3, the stress caused by the uncoordinated deformation of the inner casing 2 and the outer casing 3 can be released with multiple degrees of freedom, and compensation can be made during the structural assembly, thereby reducing the requirements for parts processing and positioning accuracy. In addition, the risk of uncoordinated thermal deformation between the pipe and the casing can be avoided.

[0044] In the pipeline air bleed structure of the aircraft engine spanning the inner and outer casings disclosed in the above embodiment, the radius r of the inner end spherical surface of the adapter sleeve 4, the radius R of the outer end spherical surface of the adapter sleeve 4, and the length L between the inner and outer end spherical surfaces of the adapter sleeve 4 can be adjusted according to the uncoordinated deformation of the inner casing 2 and the outer casing 3, so as to achieve the required structural compensation amount and adapt to the actual situation of the uncoordinated deformation of the inner casing 2 and the outer casing 3.

[0045] In the air bleed pipe structure of the aircraft engine spanning the inner and outer casings disclosed in the above embodiment, the design of the adapter sleeve 4 is used for structural compensation. The structure is simple and easy to assemble. It can form a component with the inner air bleed pipe 1, which is convenient for storage and assembly, and can improve the maintainability of the structure.

[0046] In some conceivable embodiments, in the above-mentioned air bleed pipe structure spanning the inner and outer casings of the aircraft engine, a small gap is provided between the outlet end of the inner bleed pipe 1 and the inner end of the adapter sleeve 4;

[0047] A small gap is provided between the inlet end of the external air duct 5 and the outer end of the adapter sleeve 4, which facilitates assembly while ensuring sealing.

[0048] In some feasible embodiments, in the above-mentioned aircraft engine air bleed structure spanning the inner and outer casings, the inner wall of the inlet end of the external air bleed pipe 5 has an annular limiting protrusion, and the annular limiting protrusion has a smooth transition between the inclined surface on one side of the adapter sleeve 4 and the inner wall of the inlet end of the external air bleed pipe 5, so as to limit the adapter sleeve 4 and avoid damage to the adapter sleeve 4.

[0049] In some conceivable embodiments, in the above-mentioned air bleed pipe structure spanning the inner and outer casings of the aircraft engine, the outer wall of the inlet end of the inner air bleed pipe 1 has an annular connecting edge, and the annular connecting edge is connected to the annular boss surrounding the inner air bleed hole on the inner casing 2;

[0050] The outer wall of the inlet end of the external air bleed pipe 5 has an annular connecting edge, and the annular connecting edge is connected to the annular boss surrounding the external air bleed hole on the outer casing 3.

[0051] A method for assembling an air duct structure of an aircraft engine spanning an inner and outer casing, for realizing the assembly of the air duct structure of an aircraft engine spanning an inner and outer casing disclosed in the above embodiment, comprises:

[0052] Assemble the internal air duct 1 and the adapter sleeve 4, and press the outlet end of the internal air duct 1 into the inner end of the adapter sleeve 4 by pre-cooling and pre-deforming to form an assembly;

[0053] Assemble the inner air bleed pipe 1 and the inner casing 2, connect the inlet end of the inner air bleed pipe 1 to the inner casing 2, and communicate with the inner air bleed hole opened on the inner casing 2;

[0054] Assemble the outer casing 3 and the inner casing 2, sleeve the outer casing 3 onto the outer periphery of the inner casing 2, and adjust the inner end of the adapter sleeve 4 so that it extends out from the outer air bleed hole provided on the outer casing 3;

[0055] Assemble the external air bleed pipeline 5 with the outer casing 3 , connect the inlet end of the air bleed pipeline 5 to the outer casing 3 , and adjust so that the inlet end of the air bleed pipeline 5 is sleeved on the outer end of the adapter sleeve 4 .

[0056] 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 referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0057] 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 substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A pipeline air bleed structure for an aircraft engine spanning inner and outer casings, characterized in that: include: The inner air bleed pipe (1) is arranged between the inner casing (2) and the outer casing (3), the inlet end of which is connected to the inner casing (2) and communicates with the inner air bleed hole provided on the inner casing (2), and the outer wall of the outlet end of which is spherical; The adapter sleeve (4) has one end as an inner end and the other end as an outer end, wherein the inner wall of the inner end of the adapter sleeve (4) is spherical and is sleeved on the outlet end of the inner bleed air pipeline (1); the outer wall of the outer end of the adapter sleeve (4) is spherical and extends out from the outer bleed air hole opened on the outer casing (3); The inlet end of the external air bleed pipeline (5) is connected to the outer casing (3), and the inner wall is cylindrical and sleeved on the outer end of the adapter sleeve (4).

2. The pipeline air bleed structure of the aircraft engine spanning the inner and outer casings according to claim 1 is characterized in that: There is a small gap between the outlet end of the internal air duct (1) and the inner end of the adapter sleeve (4); A small gap is provided between the inlet end of the external air duct (5) and the outer end of the adapter sleeve (4).

3. The pipeline air bleed structure of the aircraft engine spanning the inner and outer casings according to claim 1, characterized in that: The inner wall of the inlet end of the external air duct (5) is provided with an annular limiting protrusion, and a sloped surface between the side of the annular limiting protrusion facing the adapter sleeve (4) and the inner wall of the inlet end of the external air duct (5) is smoothly transitioned.

4. The pipeline air bleed structure of the aircraft engine spanning the inner and outer casings according to claim 1, characterized in that: The outer wall of the inlet end of the inner air bleed pipe (1) has an annular connecting edge, and the annular connecting edge is connected to an annular boss surrounding the inner air bleed hole on the inner casing (2); The outer wall of the inlet end of the external air bleed pipeline (5) has an annular connecting edge, and the annular connecting edge is connected to an annular boss surrounding the external air bleed hole on the outer casing (3).

5. A method for assembling an air duct structure of an aircraft engine spanning inner and outer casings, for realizing the assembly of the air duct structure of an aircraft engine spanning inner and outer casings as claimed in claim 1, characterized in that: include: Assembling the internal air duct (1) and the adapter sleeve (4), and pressing the outlet end of the internal air duct (1) into the inner end of the adapter sleeve (4) through pre-cooling and pre-deformation to form an assembly; Assembling the inner air bleed pipe (1) and the inner casing (2), connecting the inlet end of the inner air bleed pipe (1) to the inner casing (2) and communicating with the inner air bleed hole provided on the inner casing (2); Assemble the outer casing (3) and the inner casing (2), sleeve the outer casing (3) onto the outer periphery of the inner casing (2), and adjust the inner end of the adapter sleeve (4) so ​​that it protrudes from the outer air bleed hole provided on the outer casing (3); The external air bleed pipeline (5) is assembled with the outer casing (3), the inlet end of the air bleed pipeline (5) is connected to the outer casing (3), and the inlet end of the air bleed pipeline (5) is adjusted so that the inlet end of the air bleed pipeline (5) is sleeved on the outer end of the adapter sleeve (4).

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