An air bleed pipe structure spanning inner and outer casings of an aircraft engine and an assembly method thereof

Abstract

The present application belongs to the technical field of aircraft engine air bleed design, and specifically relates to a pipeline air bleed structure and assembly method for an aircraft engine spanning inner and outer casings, wherein the pipeline air bleed structure for an aircraft engine spanning inner and outer casings comprises: an inner air bleed pipeline, which is arranged between the inner casing and the outer casing, with its inlet end connected to the inner casing and communicated with the inner air bleed hole opened on the inner casing, and the outer wall of its outlet end is spherical; an adapter sleeve, one end of which is the inner end and the other end is the outer end, wherein the inner wall of the inner end of the adapter sleeve is spherical and is sleeved on the outlet end of the inner air bleed pipeline; the outer wall of the outer end of the adapter sleeve is spherical and extends from the outer air bleed hole opened on the outer casing; the outer air bleed pipeline, whose inlet end is connected to the outer casing, and the inner wall is cylindrical and is sleeved on the outer end of the adapter sleeve.

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 continuously. Accordingly, pipes are used to bleed air from the internal flow channels of aircraft engines. The diameter of the required pipes is increasing continuously, and the rigidity is increasing continuously. The pipes cross the inner and outer casings of the aircraft engine to bleed air, and will be subjected to large stresses caused by the uncoordinated deformation of the inner and outer casings. They are very likely to break, seriously affecting the safety of aircraft engine operation. This problem becomes increasingly prominent with the increase of bleed air temperature.

[0004] In order to reduce the stress of the air duct caused by the uncoordinated deformation of the inner and outer casings of the aircraft engine, the following methods are currently used: Figure 1 The structural compensation scheme shown is to set the internal air bleed line between the inner casing and the outer casing, and the inlet end of the internal air bleed line is connected to the inner casing and communicated with the internal air bleed hole opened on the inner casing; the outlet end of the internal air bleed line is connected to a pipe joint, which extends from the external air bleed hole opened on the outer casing and is connected to the inlet end of the external air bleed 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 cool and evenly distribute the high-temperature components of the aircraft engine, seal and insulate the internal disc cavity and bearing lubrication system, and adjust the axial force of the rotor. The sliding of the sealing ring along the through hole of the sealing plug and the translation of the sealing ring in the annular groove on the pipe joint can be used 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 pipelines. This technical solution has the following defects:

[0006] 1) The internal and external bleed air lines are rigidly connected. The internal bleed air line must be fixed to the inner casing, while the external bleed air line must be fixed to the outer casing. This requires high machining and positioning accuracy for assembly, making assembly difficult and prone to generating significant assembly stress. Furthermore, if the internal and external bleed air lines are too strong, there is a risk of thermal deformation mismatch between the lines and the casing, generating harmful stress and reducing structural reliability.

[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 part, 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 existing 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 provided between the inner casing and the outer casing, with its inlet end connected to the inner casing and communicating with the inner bleed air hole provided on the inner casing, and the outer wall of its outlet end is spherical;

[0013] The adapter sleeve has one end as the inner end and the other end as the outer end. 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.

[0014] Extending from the external air bleed hole on the outer casing;

[0015] 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.

[0016] According to at least one embodiment of the present application, in the aforementioned air bleed pipe structure of the aircraft engine spanning the inner and outer casings, a small gap is formed between the outlet end of the inner bleed pipe and the inner end of the adapter sleeve;

[0017] There is a small gap between the inlet end of the external air pipeline and the outer end of the adapter sleeve.

[0018] 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, 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 side facing the adapter sleeve and the inner wall of the inlet end of the external air bleed pipe.

[0019] According to at least one embodiment of the present application, in the aforementioned air bleed pipe structure spanning the inner and outer casings of an aircraft engine, the outer wall of the inlet end of the inner bleed pipe has an annular connecting edge, and the annular connecting edge is connected to an annular boss surrounding the inner bleed hole on the inner casing;

[0020] The outer wall of the inlet end of the external air bleed pipe is provided with 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.

[0021] On the other hand, a method for assembling an air bleed pipe structure of an aircraft engine spanning inner and outer casings is provided, which is used to assemble the air bleed pipe structure of the aircraft engine spanning inner and outer casings, and is characterized by comprising:

[0022] 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;

[0023] Assemble the internal bleed air pipeline with the inner casing, connect the inlet end of the internal bleed air pipeline to the inner casing, and connect it to the internal bleed air hole opened on the inner casing;

[0024] Assemble the outer casing and the inner casing, place the outer casing on the outer periphery of the inner casing, and adjust the inner end of the adapter sleeve so that it extends from the outer air bleed hole provided on the outer casing;

[0025] 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 onto the outer end of the adapter sleeve.

[0026] This application has at least the following beneficial technical effects:

[0027] Provided are an air bleed pipe structure and an assembly method for an aircraft engine that spans inner and outer casings. An inner air bleed pipe is designed to be connected to an outer air bleed pipe by using an adapter sleeve. The outlet end of the inner air bleed pipe is in spherical contact with the inner end of the adapter sleeve and can rotate relative to each other. The inlet end of the outer air bleed pipe is in cylindrical and spherical contact with the outer end of the adapter sleeve and can rotate and slide relative to each other. In this way, when the inner air bleed pipe is fixed to the inner casing and the outer air bleed pipe is fixed to the outer casing, stress generated by uncoordinated deformation of the inner and outer casings can be released with multiple degrees of freedom, and compensation can be performed during structural assembly, thereby reducing requirements for parts processing and positioning accuracy. In addition, the risk of uncoordinated thermal deformation between the pipe and the casing can be avoided. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a schematic diagram of the existing method of using pipes to bleed air from the internal flow channel of an aircraft engine;

[0029] Figure 2 This is a schematic diagram of a pipe air bleed structure spanning the inner and outer casings of an aircraft engine provided by an embodiment of the present application;

[0030] Figure 3 Schematic diagram of the internal air bleed circuit provided in an embodiment of the present application;

[0031] Figure 4 is a schematic diagram of an adapter sleeve provided in an embodiment of the present application;

[0032] Figure 5 Schematic diagram of an external air bleed pipeline provided in an embodiment of the present application;

[0033] Figure 6 Schematic diagram of compensation for the air bleed pipe structure of an aircraft engine spanning the inner and outer casings provided by an embodiment of the present application;

[0034] in:

[0035] 1-Inner air bleed line; 2-Inner casing; 3-Outer casing; 4-Adapter sleeve; 5-External air bleed line.

[0036] 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

[0037] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0038] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application 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 means 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.

[0039] In addition, it should be noted that, unless otherwise clearly stipulated 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.

[0040] An air bleed pipe structure for an aircraft engine that spans the inner and outer casings, such as Figure 2-6 Shown, including:

[0041] The inner bleed air pipeline 1 is provided between the inner casing 2 and the outer casing 3. Its inlet end is connected to the inner casing 2 and communicates with the inner bleed air hole provided on the inner casing 2. The outer wall of its outlet end is spherical.

[0042] The adapter sleeve 4 has an inner end at one end and an outer end at the other end. The inner end of the adapter sleeve 4 has a spherical inner wall and is sleeved on the outlet end of the inner bleed air pipe 1. The outer end of the adapter sleeve 4 has a spherical outer wall and extends from the outer bleed air hole provided on the outer casing 3.

[0043] The inlet end of the external air bleed pipe 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 .

[0044] In the air bleed structure of the aircraft engine spanning the inner and outer casings disclosed in the above embodiment, the inner air bleed duct 1 and the outer air bleed duct 5 are designed to be connected by using an adapter sleeve 4. The outlet end of the inner air bleed duct 1 and the inner end of the adapter sleeve 4 are in spherical fit contact and can rotate relative to each other. The inlet end of the outer air bleed duct 5 and the outer end of the adapter sleeve 4 are in cylindrical and spherical fit contact and can rotate and slide relative to each other. In this way, when the inner air bleed duct 1 is fixed to the inner casing 2 and the outer air bleed duct 5 is fixed to the outer casing 3, the stress generated 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 structural assembly, thereby reducing the requirements for parts processing and positioning accuracy. In addition, the risk of uncoordinated thermal deformation between the duct and the casing can be avoided.

[0045] In the air bleed pipe 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.

[0046] In the air bleed pipe structure of the aircraft engine spanning the inner and outer casings disclosed in the above embodiment, the design uses the relevant design of the adapter sleeve 4 for structural compensation. The structure is simple and easy to assemble, and can form a component with the internal air bleed pipe 1, which is convenient for storage and assembly, and can improve the maintainability of the structure.

[0047] 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 formed between the outlet end of the inner bleed pipe 1 and the inner end of the adapter sleeve 4;

[0048] There is a small gap between the inlet end of the external air duct 5 and the outer end of the adapter sleeve 4, which ensures sealing and facilitates assembly.

[0049] In some feasible embodiments, in the above-mentioned air bleed structure of the aircraft engine 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 the side facing 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.

[0050] 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 bleed pipe 1 has an annular connecting edge, and the annular connecting edge is connected to the annular boss surrounding the inner bleed hole on the inner casing 2;

[0051] The outer wall of the inlet end of the external air bleed pipe 5 has an annular connecting edge, which is connected to the annular boss surrounding the external air bleed hole on the outer casing 3.

[0052] A method for assembling an air bleed pipe structure spanning inner and outer casings of an aircraft engine, for implementing the assembly of the air bleed pipe structure spanning inner and outer casings of an aircraft engine disclosed in the above embodiment, comprises:

[0053] Assemble the internal air bleed pipe 1 and the adapter sleeve 4, and press the outlet end of the internal air bleed pipe 1 into the inner end of the adapter sleeve 4 through pre-cooling and pre-deformation to form an assembly;

[0054] Assemble the inner bleed air pipe 1 and the inner casing 2, connect the inlet end of the inner bleed air pipe 1 to the inner casing 2, and communicate with the inner bleed air hole opened on the inner casing 2;

[0055] Assemble the outer casing 3 and the inner casing 2, put the outer casing 3 on 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;

[0056] Assemble the external air bleed pipe 5 and the outer casing 3 , connect the inlet end of the air bleed pipe 5 to the outer casing 3 , and adjust so that the inlet end of the air bleed pipe 5 is sleeved onto the outer end of the adapter sleeve 4 .

[0057] 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.

[0058] 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 pipeline air bleed structure spanning the inner and outer casings of an aircraft engine, characterized in that: include: An inner air bleed pipe (1) is provided between the inner casing (2) and the outer casing (3), an inlet end of which is connected to the inner casing (2) and communicates with an inner air bleed hole provided on the inner casing (2), and an outer wall of an 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 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 from the outer bleed air hole provided on the outer casing (3); The inlet end of the external air bleed pipe (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).

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

3. The air bleed pipe structure for an aircraft engine spanning 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 smooth bevel transition is formed 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).

4. The air bleed pipe structure for an aircraft engine spanning 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 the 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 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).

5. A method for assembling an air bleed pipe structure spanning inner and outer casings of an aircraft engine, for assembling the air bleed pipe structure spanning inner and outer casings of an aircraft engine according to claim 1, characterized in that: include: Assembling the internal air bleed pipe (1) and the adapter sleeve (4), pressing the outlet end of the internal air bleed pipe (1) into the inner end of the adapter sleeve (4) through pre-cooling and pre-deformation to form an assembly; 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 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 extends out from the outer air bleed hole provided on the outer casing (3); The external air bleed pipe (5) is assembled with the outer casing (3), the inlet end of the external air bleed pipe (5) is connected to the outer casing (3), and the inlet end of the external air bleed pipe (5) is adjusted so that the inlet end of the external air bleed pipe (5) is sleeved on the outer end of the adapter sleeve (4).

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