阅读说明：本技术 一种航空发动机单涵道高低压气机及其中介机匣部件 (Single-duct high-low pressure air machine of aircraft engine and intermediate casing part thereof ) 是由 国睿 刘杰 郭海宁 昌皓 吴松洋 于 2021-10-27 设计创作，主要内容包括：本申请属于航空发动机单涵道高低压气机及其中介机匣部件设计领域,具体涉及一种航空发动机单涵道高低压气机及其中介机匣部件,包括：低压压气机,低压压气机出口处的最后一排叶片为转子叶片；中介机匣部件,中介机匣部件的进口与低压压气机的出口对接,其内各个支板的前缘沿逆低压压气机出口处最后一排叶片的扭转方向弯曲；高压压气机,高压压气机的进口与中介机匣部件的出口对接。(The application belongs to the design field of single duct high-low pressure mechanism of aeroengine and intermediary machine casket part thereof, concretely relates to single duct high-low pressure mechanism of aeroengine and intermediary machine casket part thereof includes: the last row of blades at the outlet of the low-pressure compressor are rotor blades; the front edges of all supporting plates in the intermediate casing component are bent along the twisting direction of the last row of blades at the outlet of the low-pressure compressor; and the inlet of the high-pressure compressor is butted with the outlet of the intermediate casing part.)

1. The utility model provides an aeroengine list duct high-low pressure machine and intermediary machine casket part thereof which characterized in that includes:

the last row of blades at the outlet of the low-pressure compressor (1) are rotor blades;

the inlet of the intermediate casing component (2) is butted with the outlet of the low-pressure compressor (1), and the front edge of each support plate (3) is bent along the direction opposite to the torsion direction of the last row of blades at the outlet of the low-pressure compressor (1);

and an inlet of the high-pressure compressor (4) is butted with an outlet of the intermediate casing component (2).

2. The aircraft engine single duct high-low pressure gas engine and its intermediary casing component according to claim 1,

the outer casing (5) and the inner casing (6) at the inlet of the intermediate casing part (2) are straight sections.

3. The aircraft engine single duct high-low pressure gas engine and its intermediary casing component according to claim 1,

the outer casing (5) and the inner casing (6) at the outlet of the intermediate casing component (2) are straight sections.

4. The aircraft engine single duct high-low pressure gas engine and its intermediary casing component according to claim 1,

the length of the curved part of the front edge of each support plate (3) is 1/3-1/2 of the total length.

Technical Field

The application belongs to the field of design of single-duct high-low pressure air engines of aircraft engines and intermediate casing parts thereof, and particularly relates to a single-duct high-low pressure air engine of an aircraft engine and an intermediate casing part thereof.

Background

The compression system in the aircraft engine is generally composed of a low-pressure compressor and a high-pressure compressor which are coaxially arranged, wherein, the inner and outer diameters of the outlet of the low-pressure compressor are higher than the inner and outer diameters of the inlet of the high-pressure compressor, an intermediate casing part is designed between the outlet of the low-pressure compressor and the inlet of the high-pressure compressor, an intermediate casing channel which is composed of an outer casing, an inner casing and a support plate arranged between the outer casing and the inner casing along the circumferential direction in the intermediate casing part bends the airflow flowing out from the outlet of the low-pressure compressor to the inlet of the high-pressure compressor, as shown in fig. 1, after the air flow in the low-pressure compressor is pressurized by the last stage rotor blade, a circumferential velocity exists, and after the air flow is rectified by the last stage stator blade, the circumferential velocity is greatly reduced and approaches to 0, and then flows out of the outlet to the inlet of the high pressure compressor through the intermediate casing channel, as shown in fig. 2.

The structure formed by a high-low pressure machine and an intermediate casing part thereof in the single-duct aircraft engine is defined as follows:

wherein: gamma is the compactness of the intermediate casing part; r1 is the average radius of the low pressure compressor outlet; r2 is the average inlet radius of the inlet of the high-pressure compressor; l is the axial length of the intermediate casing flow channel.

The larger the compactness degree gamma of the intermediate casing part is, the more easily the air flow flowing through the intermediate casing channel is subjected to flow separation, the lower the aerodynamic performance is, in order to ensure the aerodynamic performance of the air flow flowing through the intermediate casing channel, under the condition that the average radius R1 of the outlet of the low-pressure air compressor and the average radius R2 of the inlet of the high-pressure air compressor are certain, the axial length L of the intermediate casing channel is more required to be designed to be longer, namely the overall length of the intermediate casing part is required to be designed to be longer, the compactness degree gamma of the intermediate casing part is difficult to improve, and the overall length and the mass of the single-duct aero-engine are larger.

The present application has been made in view of the above-mentioned technical drawbacks.

It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.

Disclosure of Invention

The application aims to provide a single-duct high-low pressure air machine of an aircraft engine and an intermediate casing structure thereof, so as to overcome or alleviate technical defects of at least one known aspect.

The technical scheme of the application is as follows:

an aeroengine single duct high-low pressure machine and intermediary cartridge receiver part thereof includes:

the last row of blades at the outlet of the low-pressure compressor are rotor blades;

the front edges of all supporting plates in the intermediate casing component are bent along the twisting direction of the last row of blades at the outlet of the low-pressure compressor;

and the inlet of the high-pressure compressor is butted with the outlet of the intermediate casing part.

According to at least one embodiment of the application, in the single-duct high-low pressure gas engine of the aircraft engine and the intermediate casing component thereof, the outer casing and the inner casing at the inlet of the intermediate casing component are straight sections.

According to at least one embodiment of the application, in the single-duct high-low pressure gas engine of the aircraft engine and the intermediate casing component thereof, the outer casing and the inner casing at the outlet of the intermediate casing component are straight sections.

According to at least one embodiment of the application, in the aircraft engine single-bypass high-low pressure compressor and the intermediate casing component thereof, the length of the bent part of the front edge of each support plate is 1/3-1/2 of the total length.

The application has at least the following beneficial technical effects:

the last row of stator blades at the position of an original low-pressure gas outlet and each support plate in the intermediate casing part are integrally designed, so that each support plate in the intermediate casing part has the functions of rectification and flow guiding, the overall length and the mass of the single-duct aero-engine can be reduced to a certain extent, the airflow flowing path is more gentle, the capability of resisting airflow flowing separation is higher, the overall length of the intermediate casing part can be designed to be shorter, and the compactness of the intermediate casing part is improved.

Drawings

FIG. 1 is a schematic diagram of a single-duct high-low pressure gas engine and its intermediate casing components of a prior art aircraft engine;

FIG. 2 is a schematic view of the flow of air flow in a single-duct high-low pressure air machine and its intermediate casing component of a conventional aircraft engine;

FIG. 3 is a schematic diagram of a single-duct high-low pressure compressor of an aircraft engine and its intermediate casing components provided by an embodiment of the present application;

FIG. 4 is a schematic view of the flow of the gas in the single-duct high-low pressure gas engine and its intermediate casing component of the aircraft engine provided by the embodiment of the present application;

wherein:

1-a low-pressure compressor; 2-an intermediate casing part; 3-a support plate; 4-high pressure compressor; 5-an outer casing; 6-inner casing.

For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.

Detailed Description

In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.

In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.

Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.

The present application is described in further detail below with reference to fig. 1 to 4.

An aeroengine single duct high-low pressure machine and intermediary cartridge receiver part thereof includes:

the last row of blades at the outlet of the low-pressure compressor 1 are rotor blades;

the inlet of the intermediate casing part 2 is butted with the outlet of the low-pressure compressor 1, and the front edges of the support plates 3 in the intermediate casing part are bent along the direction opposite to the twisting direction of the last row of blades at the outlet of the low-pressure compressor 1;

and an inlet of the high-pressure compressor 4 is butted with an outlet of the intermediate casing part 2.

For the aero-engine single-duct high-low pressure compressor and its intermediate casing components disclosed in the above embodiments, it can be understood by those skilled in the art that the last row of blades at the outlet of the low pressure compressor 1 is designed as rotor blades, namely, the last row of stator blades at the outlet of the original low-pressure compressor 1 is cancelled, and the front edges of all support plates 3 in the intermediate casing component 2 are designed to be bent along the twisting direction of the last row of blades at the outlet of the inverse low-pressure compressor 1, the last row of stator blades at the outlet of the low-pressure compressor 1 are bent along the twisting direction of the last row of rotor blades, namely, the last row of stator blades at the outlet of the original low-pressure compressor and all supporting plates in the intermediate casing part are integrally designed, so that all the supporting plates 3 in the intermediate casing part 2 have the functions of rectification and flow guiding at the same time, and the overall length and the mass of the single-duct aero-engine can be reduced to a certain extent.

For the single-duct high-low pressure air compressor of the aircraft engine and the intermediate casing part thereof disclosed in the above embodiments, it can be understood by those skilled in the art that after the air flow in the low-pressure air compressor 1 is pressurized by the last stage of rotor blades, has circumferential speed, directly flows into the intermediate casing flow passage, and generates circumferential flow and circumferential deflection along each support plate 3, and then flows to the inlet of the high pressure compressor 4, making the flow path of the gas flow more gradual, with greater resistance to flow separation of the gas flow, as shown in figure 4, under the condition that the average radius R1 of the outlet of the low-pressure compressor 1 and the average radius R2 of the inlet of the high-pressure compressor 2 are fixed, the axial length L of the flow channel of the intermediate casing can be designed to be shorter, that is, the overall length of the intermediate casing member 2 is designed to be short, so that the degree of compactness γ of the intermediate casing member can be increased, and the overall length and mass of the single-duct aircraft engine can be further reduced.

In some optional embodiments, in the single-duct high-low pressure gas engine of the aircraft engine and the intermediate casing part thereof, the outer casing 5 and the inner casing 6 at the inlet of the intermediate casing part 2 are straight sections, so that the gas flow flowing from the outlet of the low-pressure gas compressor 1 to the inlet of the intermediate casing part 2 is smooth, and the outer casing 5 and the inner casing 6 at the inlet of the intermediate casing part 2 may also be designed to have a certain slope according to actual requirements.

In some optional embodiments, in the single-duct high-low pressure gas engine of the aircraft engine and the intermediate casing part thereof, the outer casing 5 and the inner casing 6 at the outlet of the intermediate casing part 2 are straight sections, so that the gas flow flowing from the outlet of the intermediate casing part 2 to the inlet of the high-pressure gas compressor 2 flows smoothly, and the outer casing 5 and the inner casing 6 at the outlet of the intermediate casing part 2 may also be designed to have a certain slope according to actual requirements.

In some alternative embodiments, in the single-duct high-low pressure compressor of an aircraft engine and its intermediate casing component, the length of the curved portion of the front edge of each strut 3 is 1/3-1/2 of the total length, and when the technical solution disclosed in this application is applied, the length of the curved portion of the front edge of each strut 3 can be designed according to the actual situation, and the length of the curved portion can be expanded to the range of the total length of the strut.

The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.

Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.