CN113864239A - Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof - Google Patents
Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof Download PDFInfo
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- CN113864239A CN113864239A CN202111257690.5A CN202111257690A CN113864239A CN 113864239 A CN113864239 A CN 113864239A CN 202111257690 A CN202111257690 A CN 202111257690A CN 113864239 A CN113864239 A CN 113864239A
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- intermediate casing
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- pressure compressor
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- 238000010586 diagram Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000004323 axial length Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
Abstract
The application belongs to two duct aeroengine high-low pressure machines and intermediary machine casket part design field, concretely relates to two duct aeroengine high-low pressure machines and intermediary machine casket part thereof includes: the last row of blades at the outlet of the low-pressure compressor are rotor blades; the inlet of the intermediate casing part is butted with the outlet of the low-pressure compressor, the front edges of the support plates in the intermediate casing part are bent along the twisting direction of the last row of blades at the outlet of the low-pressure compressor, an intermediate casing outer flow channel is formed between the inner splitter ring and the outer casing of the intermediate casing part, and an intermediate casing inner flow channel is formed between the inner casing of the intermediate casing part and the outer casing of the intermediate casing part; and an inlet of the high-pressure compressor is butted with an outlet of the flow channel in the intermediate casing.
Description
Technical Field
The application belongs to the field of design of a double-duct aero-engine high-low pressure air machine and an intermediary casing component thereof, and particularly relates to a double-duct aero-engine high-low pressure air machine and an intermediary casing component thereof.
Background
A compression system in an aircraft engine generally comprises a low-pressure compressor and a high-pressure compressor which are coaxially arranged, wherein the inner diameter and the outer diameter of an outlet of the low-pressure compressor are higher than the inner diameter and the outer diameter of an 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, a shunting ring is arranged in the intermediate casing part and divides an internal flow passage of the intermediate casing into an intermediate casing internal flow passage and an intermediate casing external flow passage, wherein the intermediate casing internal flow passage bends airflow flowing out from the outlet of the low-pressure compressor to the inlet of the high-pressure compressor, as shown in figure 1, after the airflow in the low-pressure compressor is pressurized by a last stage rotor blade, a circumferential velocity exists, after the airflow is rectified by the last stage stator blade, the circumferential velocity is greatly reduced and approaches to 0, and then flows out from the outlet, and part of the airflow flows out from the intermediate casing external flow passage, and part of the gas flows to the inlet of the high-pressure compressor through the flow channel in the intermediate casing, as shown in fig. 2.
The structure formed by a high-low pressure machine and an intermediate casing part thereof in the double-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 dual-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
It is an object of the present application to provide a dual ducted aircraft engine high and low pressure gas engine and its intervening casing components to overcome or alleviate at least one of the technical deficiencies of the known prior art.
The technical scheme of the application is as follows:
a kind of double ducted aeroengine high-low pressure machine and intermediary cartridge receiver part, including:
the last row of blades at the outlet of the low-pressure compressor are rotor blades;
the inlet of the intermediate casing part is butted with the outlet of the low-pressure compressor, the front edges of the support plates in the intermediate casing part are bent along the twisting direction of the last row of blades at the outlet of the low-pressure compressor, an intermediate casing outer flow channel is formed between the inner splitter ring and the outer casing of the intermediate casing part, and an intermediate casing inner flow channel is formed between the inner casing of the intermediate casing part and the outer casing of the intermediate casing part;
and an inlet of the high-pressure compressor is butted with an outlet of the flow channel in the intermediate casing.
According to at least one embodiment of the application, in the aircraft engine double-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.
According to at least one embodiment of the application, in the aircraft engine double-duct high-low pressure air machine and the intermediate casing part thereof, the rear edge of each support plate is provided with a notch;
the front edge of the diverter ring is clamped into each notch.
According to at least one embodiment of the application, in the aircraft engine double-duct high-low pressure air engine and the intermediate casing component thereof, the front edge of the splitter ring is provided with a plurality of positioning openings distributed along the circumferential direction;
the rear edge of each support plate is correspondingly clamped into one positioning hole.
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 double-duct aero-engine can be reduced to a certain degree, in addition, the air flow path can be more gentle, the capacity of resisting the flow separation of air flow is high, the overall length of the intermediate casing part can be designed to be shorter, and the compactness gamma of the intermediate casing part is improved.
Drawings
FIG. 1 is a schematic diagram of a high-low pressure air machine of a prior art double-duct aircraft engine and an intermediate casing component thereof;
FIG. 2 is a schematic view of the flow of air streams in the high-low pressure air engine and its intermediate casing components of a prior art dual-duct aircraft engine;
FIG. 3 is a schematic diagram of a dual-duct aircraft engine high-low pressure compressor and its intervening casing components provided by an embodiment of the present application;
FIG. 4 is a schematic diagram illustrating the flow of gas streams within a dual-duct aircraft engine high and low pressure gas engine and its intervening casing components provided by an embodiment of the present application;
wherein:
1-a low-pressure compressor; 2-an intermediate casing part; 3-a support plate; 4-a shunt ring; 5-an outer casing; 6-inner casing; 7-a high-pressure compressor;
a-intermediate casing external flow channel;
b-intermediate casing inner flow passage.
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.
A kind of double ducted aeroengine high-low pressure machine and intermediary cartridge receiver part, including:
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, the front edges of the support plates 3 in the intermediate casing part are bent along the twisting direction of the last row of blades at the outlet of the low-pressure compressor 1, an intermediate casing outer flow channel A is formed between the inner splitter ring 4 and the outer casing 5 of the intermediate casing part, and an intermediate casing inner flow channel B is formed between the inner casing 6 of the intermediate casing part and the outer casing 5 of the intermediate casing part;
and an inlet of the high-pressure compressor 7 is butted with an outlet of the flow channel B in the intermediate casing.
For the dual-duct aero-engine high-low pressure engine and the intermediate casing component thereof 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 bending is carried out along the torsion direction of the last row of rotor blades at the outlet of the low-pressure gas compressor 1, namely, the last row of stator blades at the outlet of the original low-pressure gas 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 double-duct aero-engine can be reduced to a certain extent.
For the dual-duct aero-engine high-low pressure engine and the intermediate casing component thereof disclosed in the above embodiments, it can be further understood by those skilled in the art that after the air flow in the low pressure compressor 1 is pressurized by the last stage of rotor blade, the air flow has a circumferential velocity, and directly flows into the intermediate casing channel, and flows circumferentially and turns circumferentially along each support plate 3, and then flows out through the intermediate casing outer channel a, and flows to the inlet of the high pressure compressor 7 through the intermediate casing inner channel B, so that the air flow path is more smooth, and has a greater ability to resist the flow separation of the air flow, as shown in fig. 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 7 are fixed, the axial intermediate length L of the intermediate casing channel can be designed to be shorter, that is, the overall length of the intermediate casing component 2 is designed to be shorter, therefore, the compactness degree gamma of the intermediate casing part can be improved, and the overall length and the overall mass of the double-duct aircraft engine can be further reduced.
In some alternative embodiments, in the aircraft engine dual-duct high-low pressure compressor 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 specific practice, and the length of the curved portion can be expanded to the range of the total length of the strut.
In some alternative embodiments, in the aircraft engine dual-duct high-low pressure air engine and its intermediate casing component, the rear edge of each support plate 3 has a notch;
the front edge of the shunt ring 4 is clamped into each notch, so that the shunt ring 4 and each support plate 3 in the intermediary casing part 2 are reliably fixed.
In some optional embodiments, in the aircraft engine dual-duct high-low pressure gas engine and the intermediate casing component thereof, the front edge of the splitter ring 4 has a plurality of positioning ports distributed along the circumferential direction;
the rear edge of each support plate 3 is correspondingly clamped into one positioning opening, so that the shunting ring 4 in the intermediate casing part 2 is reliably fixed with each support plate 3.
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.
Claims (4)
1. The utility model provides a two duct aeroengine high-low pressure machines 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 part (2) is butted with the outlet of the low-pressure compressor (1), 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), an intermediate casing outer flow channel (A) is formed between the inner splitter ring (4) and the outer casing (5) of the intermediate casing part, and an intermediate casing inner flow channel (B) is formed between the inner casing (6) of the intermediate casing part;
and an inlet of the high-pressure compressor (7) is butted with an outlet of the intermediate casing inner flow channel (B).
2. The aircraft engine dual-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.
3. The aircraft engine dual-duct high-low pressure gas engine and its intermediary casing component according to claim 1,
the rear edge of each support plate (3) is provided with a notch;
the front edge of the shunting ring (4) is clamped into each notch.
4. The aircraft engine dual-duct high-low pressure gas engine and its intermediary casing component according to claim 1,
the front edge of the splitter ring (4) is provided with a plurality of positioning openings distributed along the circumferential direction;
the rear edge of each support plate (3) is correspondingly clamped into one positioning opening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111257690.5A CN113864239A (en) | 2021-10-27 | 2021-10-27 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111257690.5A CN113864239A (en) | 2021-10-27 | 2021-10-27 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
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| CN113864239A true CN113864239A (en) | 2021-12-31 |
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| CN202111257690.5A Pending CN113864239A (en) | 2021-10-27 | 2021-10-27 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114542518A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Double-duct compressor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108691583A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Casing among turbogenerator |
| CN109854377A (en) * | 2019-04-08 | 2019-06-07 | 沈阳建筑大学 | A kind of novel aerial turbo fan engine |
| CN109854378A (en) * | 2019-04-08 | 2019-06-07 | 沈阳建筑大学 | A kind of turbofan with mode tuning ability |
| CN110735672A (en) * | 2019-10-11 | 2020-01-31 | 中国航发沈阳发动机研究所 | shunt ring and intermediate casing sector section structure with same |
| CN111219265A (en) * | 2020-02-14 | 2020-06-02 | 中国航发沈阳发动机研究所 | Variable cycle engine mode control mechanism and intermediate casing structure with same |
| CN111594316A (en) * | 2020-05-11 | 2020-08-28 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver assembly |
| CN112648026A (en) * | 2020-12-16 | 2021-04-13 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver structure |
-
2021
- 2021-10-27 CN CN202111257690.5A patent/CN113864239A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108691583A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Casing among turbogenerator |
| CN109854377A (en) * | 2019-04-08 | 2019-06-07 | 沈阳建筑大学 | A kind of novel aerial turbo fan engine |
| CN109854378A (en) * | 2019-04-08 | 2019-06-07 | 沈阳建筑大学 | A kind of turbofan with mode tuning ability |
| CN110735672A (en) * | 2019-10-11 | 2020-01-31 | 中国航发沈阳发动机研究所 | shunt ring and intermediate casing sector section structure with same |
| CN111219265A (en) * | 2020-02-14 | 2020-06-02 | 中国航发沈阳发动机研究所 | Variable cycle engine mode control mechanism and intermediate casing structure with same |
| CN111594316A (en) * | 2020-05-11 | 2020-08-28 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver assembly |
| CN112648026A (en) * | 2020-12-16 | 2021-04-13 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114542518A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Double-duct compressor |
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