An aero-engine compressor fulcrum bleed air sealing structure

Abstract

The present application belongs to the technical field of design of front pivot air bleed seal for aircraft engine compressor, and specifically relates to an aircraft engine compressor pivot air bleed seal structure, including: an air collecting box connected to the outside of the compressor casing; an air supply pipe penetrating the side wall of the compressor casing and connecting the air collecting box and the rear pivot sealing cavity; a rear air supply hole is provided on the side wall of the rear shaft neck of the compressor rotor; the rear air supply hole connects the rear pivot sealing cavity and the inside of the rear shaft neck of the compressor rotor; a front air supply hole is provided on the side wall of the front shaft neck of the compressor rotor; the front air supply hole connects the front pivot sealing cavity and the inside of the front shaft neck of the compressor rotor.

Description

Technical Field

[0001] The present application belongs to the technical field of design of front pivot air bleed seal for aircraft engine compressor, and specifically relates to a pivot air bleed seal structure for aircraft engine compressor. Background Art

[0002] In an aircraft engine, the front end of the compressor rotor is supported on the inner side of the front bearing casing by a front pivot bearing sleeved on the front journal, and the rear end is supported on the inner side of the rear bearing casing by a rear pivot bearing sleeved on the rear journal. In order to lubricate and cool the front pivot bearing and the rear pivot bearing, a front pivot lubricating oil cavity and a rear pivot lubricating oil cavity are constructed, wherein:

[0003] The front pivot bearing is located in the front pivot oil cavity, which is composed of the compressor cap, the compressor rotor front journal, a baffle arranged in the compressor rotor front journal, and the front sealing edge on the inner ring of the compressor support plate, and a graphite sealing device arranged between the front sealing edge and the compressor rotor front journal. A front pivot oil tank is arranged on the outer side of the compressor casing, and the front pivot oil tank supplies oil to the front pivot oil cavity through the front pivot oil supply pipe that runs through the compressor support plate and its inner ring, so as to lubricate and cool the front pivot bearing. In order to prevent the oil in the front pivot oil cavity from leaking from the graphite sealing device, a front grate coating sealing structure is arranged between the front sealing edge and the compressor rotor front journal, and a front pivot sealing cavity is formed between the front sealing edge and the graphite sealing device, and a gas seal is introduced from the front section of the compressor through the front pivot air duct for sealing;

[0004] The rear pivot bearing is located in the rear pivot oil cavity, which is composed of the rear bearing casing, the rear shaft neck of the compressor rotor, and a spiral sealing device arranged between the rear bearing casing and the rear shaft neck of the compressor rotor. A rear pivot oil tank is arranged on the outside of the compressor casing, and the rear pivot oil tank supplies oil to the rear pivot oil cavity through the rear pivot oil supply pipe to lubricate and cool the rear pivot bearing. In order to prevent the oil in the rear pivot oil cavity from leaking from the spiral sealing device, a rear grate coating sealing structure is arranged between the rear bearing casing and the rear shaft neck of the compressor rotor, and a rear pivot sealing cavity is formed between the rear bearing casing and the rear shaft neck of the compressor rotor, and gas is introduced from the rear section of the compressor through the rear pivot air duct to seal.

[0005] Currently, in large-flow, small-hub-ratio compressors, the space in the area where the front pivot bearing is located is small. In order to facilitate the arrangement of related structures, the front pivot bearing is relatively moved backward to shorten the span between the front pivot bearing and the rear pivot bearing. However, this technical solution causes the path for introducing gas from the front section of the compressor to seal the front pivot sealing cavity to be too long, resulting in large pressure loss, making it difficult to achieve an effective sealing effect.

[0006] This application is proposed in view of the above-mentioned technical defects.

[0007] 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 the present application. Summary of the invention

[0008] The purpose of the present application is to provide an aircraft engine compressor pivot bleed air sealing structure to overcome or alleviate at least one aspect of the known technical defects.

[0009] The technical solution of this application is:

[0010] An aero-engine compressor pivot bleed air sealing structure, comprising:

[0011] The air collecting box is connected to the outside of the compressor casing;

[0012] The air supply pipe is arranged through the side wall of the compressor casing and connected with the air collecting box and the rear support sealing cavity;

[0013] A rear air supply hole is provided on the side wall of the rear journal of the compressor rotor; the rear air supply hole is connected to the rear support point sealing cavity and the rear journal of the compressor rotor;

[0014] A front air supply hole is provided on the side wall of the front journal of the compressor rotor; the front air supply hole is connected with the front support point sealing cavity and the front journal of the compressor rotor.

[0015] According to at least one embodiment of the present application, in the above-mentioned aircraft engine compressor pivot bleed air sealing structure, the air collecting box is annular and sleeved on the outside of the compressor casing;

[0016] There are multiple air supply pipes and their corresponding rear air supply holes and front air supply holes, which are distributed along the circumference of the compressor.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine compressor pivot bleed air sealing structure, each rear air supply hole and front air supply hole is elliptical.

[0018] According to at least one embodiment of the present application, the above-mentioned aircraft engine compressor pivot bleed air sealing structure further includes:

[0019] The external air duct connects the air collecting box and the external air source of the compressor.

[0020] According to at least one embodiment of the present application, the above-mentioned aircraft engine compressor pivot bleed air sealing structure further includes:

[0021] The internal air bleed duct connects the air collecting box and the end of the compressor flow channel. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 is a schematic diagram of an aero-engine compressor pivot bleed air sealing structure provided in an embodiment of the present application;

[0023] in:

[0024] 1- compressor rotor; 2- front pivot bearing; 3- front bearing casing; 5- rear bearing casing; 6- compressor cap; 7- baffle; 8- compressor support plate inner ring; 9- graphite sealing device; 10- compressor casing; 11- front pivot oil box; 12- compressor support plate; 13- front pivot oil supply pipe; 14- front grate coating sealing structure; 15- spiral sealing device; 16- rear grate coating sealing structure; 17- air collecting box; 18- air supply pipe; 19- external air bleed pipe; 20- internal air bleed pipe;

[0025] A- front pivot oil cavity;

[0026] B- rear pivot lubricating oil cavity;

[0027] C- front fulcrum seal cavity;

[0028] D- Rear pivot seal cavity.

[0029] 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 cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0030] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with 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. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0032] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" 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 the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0033] The following is combined with Figure 1 This application is described in further detail.

[0034] An aero-engine compressor pivot bleed air sealing structure, comprising:

[0035] The air collecting box 17 is connected to the outside of the compressor casing 10;

[0036] The air supply pipe 18 is arranged through the side wall of the compressor casing 10 and is connected to the air collecting box 17 and the rear support sealing cavity D;

[0037] A rear air supply hole is provided on the side wall of the rear journal of the compressor rotor 1; the rear air supply hole is connected to the rear pivot sealing cavity D and the rear journal of the compressor rotor 1;

[0038] A front air supply hole is provided on the side wall of the front journal of the compressor rotor 1; the front air supply hole is connected to the front support sealing cavity C and the front journal of the compressor rotor 1.

[0039] As for the aircraft engine compressor pivot air bleed sealing structure disclosed in the above-mentioned embodiment, it can be understood by technicians in the field that when the compressor is working, the gas in the air collecting box 17 can enter the rear pivot sealing cavity D through the air supply pipe 18 to achieve the sealing of the rear pivot oil cavity B, and at the same time can enter the rear shaft neck and the front shaft neck of the compressor rotor 1 through the rear air supply hole, and then enter the front pivot sealing cavity C through the front air supply hole to achieve the sealing of the front pivot oil cavity A. The sealing of the front pivot oil cavity A and the rear pivot oil cavity B are integrated, and the overall structure is simple, easy to process, manufacture and assemble, and the internal space of the rear shaft neck and the front shaft neck of the compressor rotor 1 is utilized to supply air from the rear section of the compressor to achieve the sealing of the front pivot oil cavity A, which does not occupy additional space, and the gas path is short and the pressure loss is small, which can ensure the sealing effect of the front pivot oil cavity A.

[0040] In some optional embodiments, in the above-mentioned aircraft engine compressor pivot bleed air sealing structure, the air collecting box 17 is annular and sleeved on the outside of the compressor casing 10;

[0041] There are multiple air supply pipes 18 and their corresponding rear air supply holes and front air supply holes, which are distributed along the circumference of the compressor to reduce the pressure loss of the gas along the way, ensure the sealing effect of the front support oil cavity A and the rear support oil cavity B, and the uniformity of the sealing in the circumferential direction.

[0042] In some optional embodiments, in the above-mentioned aircraft engine compressor pivot bleed air sealing structure, each rear air supply hole and front air supply hole is elliptical.

[0043] In some optional embodiments, the above-mentioned aircraft engine compressor pivot bleed air sealing structure further includes:

[0044] The external air bleed pipe 19 is connected to the air collecting box 17 and the external air source of the compressor so as to bleed air from the outside of the compressor and seal the front support lubricating oil cavity A and the rear support lubricating oil cavity B.

[0045] In some optional embodiments, the above-mentioned aircraft engine compressor pivot bleed air sealing structure further includes:

[0046] The internal air bleed pipe 20 is connected to the air collecting box 17 and the end of the compressor flow passage, so as to be able to take in air from the end of the compressor flow passage to seal the front support oil chamber A and the rear support oil chamber B. When used in specific applications, the pipeline is opened and closed according to specific actual conditions. For example, when the external air source of the compressor is not sufficient or the pressure is insufficient, it can be opened to supplement the air source.

[0047] 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.

[0048] 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. An aircraft engine compressor pivot bleed air sealing structure, wherein the front end of the compressor rotor (1) is supported on the inner side of a front bearing casing (3) by a front pivot bearing (2) sleeved on the front journal, and the rear end is supported on the inner side of a rear bearing casing (5) by a rear pivot bearing sleeved on the rear journal, and is constructed with a front pivot lubricating oil cavity (A) and a rear pivot lubricating oil cavity (B), wherein: The front pivot bearing (2) is located in the front pivot lubricating oil chamber (A), and the rear pivot bearing is located in the rear pivot lubricating oil chamber (B), and the front pivot lubricating oil chamber (A) and the rear pivot lubricating oil chamber (B) are provided with a front pivot sealing chamber (C) and a rear pivot sealing chamber (D); The aero-engine compressor pivot bleed air sealing structure is characterized by comprising: An air collecting box (17) connected to the outside of the compressor casing (10); An air supply pipe (18) is arranged to penetrate the side wall of the air supply compressor casing (10) and is connected to the air collecting box (17) and the rear support sealing cavity (D); A rear air supply hole is provided on the side wall of the rear journal of the compressor rotor (1); the rear air supply hole is connected to the rear support point sealing cavity (D) and the rear journal of the compressor rotor (1); A front air supply hole is provided on the side wall of the front journal of the compressor rotor (1); the front air supply hole is connected to the front support point sealing cavity (C) and the interior of the front journal of the compressor rotor (1); When the compressor is working, the gas in the air collecting box (17) can enter the rear support sealing chamber (D) through the air supply pipe (18), thereby sealing the rear support lubricating oil chamber (B). At the same time, it can enter the rear journal and the front journal of the compressor rotor (1) through the rear air supply hole, and then enter the front support sealing chamber (C) through the front air supply hole, thereby sealing the front support lubricating oil chamber (A).

2. The aircraft engine compressor fulcrum bleed air sealing structure according to claim 1, characterized in that: The air collecting box (17) is annular and sleeved on the outside of the compressor casing (10); There are a plurality of air supply pipes (18) and their corresponding rear air supply holes and front air supply holes, which are distributed along the circumference of the compressor.

3. The aircraft engine compressor fulcrum bleed air sealing structure according to claim 2, characterized in that: Each rear air supply hole and front air supply hole is elliptical.

4. The aircraft engine compressor fulcrum bleed air sealing structure according to claim 1, characterized in that: Also includes: The external air bleed pipe (19) is connected to the air collecting box (17) and the external air source of the compressor.

5. The aircraft engine compressor fulcrum bleed air sealing structure according to claim 1, characterized in that: Also includes: The internal air bleed pipe (20) is connected to the air collecting box (17) and the end of the compressor flow channel.

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