CN116085073A - Final stage air-entraining structure of low-pressure fan of aero-engine - Google Patents
Final stage air-entraining structure of low-pressure fan of aero-engine Download PDFInfo
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- CN116085073A CN116085073A CN202310105986.8A CN202310105986A CN116085073A CN 116085073 A CN116085073 A CN 116085073A CN 202310105986 A CN202310105986 A CN 202310105986A CN 116085073 A CN116085073 A CN 116085073A
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- ring
- pressure fan
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- air
- protruding part
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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Abstract
The application belongs to aeroengine low pressure fan final stage bleed air structural design technical field, concretely relates to aeroengine low pressure fan final stage bleed air structure includes: the gas guiding ring is arranged on the inner side of the inner ring of the final-stage stator; the inner side of the front end of the gas guiding ring is tightly sealed with the annular boss on the final-stage rotor disk through a castor tooth coating; the rear end of the gas guiding ring is provided with an inward annular folded edge, and the annular folded edge is connected to the end face of the front end of the support plate ring in the intermediate case through bolts; the outer wall of the rear end of the air guiding ring is provided with a plurality of protruding parts distributed along the circumferential direction, the front side of each protruding part is provided with an air guiding hole communicated to the air guiding ring, each protruding part is correspondingly positioned on the front side of one support plate in the intermediate case, and the width of each protruding part is smaller than that of the corresponding support plate.
Description
Technical Field
The application belongs to the technical field of final stage bleed air structure design of low-pressure fans of aeroengines, and particularly relates to a final stage bleed air structure of low-pressure fans of aeroengines.
Background
In an aeroengine, the performance and efficiency of a low-pressure fan are improved, the exhaust temperature of the engine can be obviously reduced, the service life of the aeroengine is prolonged, the low-pressure axial force can be changed under the condition that a low-pressure turbine cannot be improved at the same time, therefore, the low-pressure fan is designed to bleed air between a final-stage rotor blade and a stator blade of the low-pressure fan, partial air flow of a main runner of the low-pressure fan is introduced into a fan disc shaft, and then is led out to the root of a primary rotor blade of the fan through a hole on the fan disc shaft, and flows back to the main runner through a gap at the root of the primary rotor blade of the fan, as shown in fig. 1, the low-pressure axial force is adjusted, the low-pressure axial force is easily caused by the technical scheme, the condition that light load or reverse direction occurs on the rear cavity pressure of the final-stage disc of the low-pressure fan cannot meet the requirement of the low-pressure axial force.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine low pressure fan last stage bleed air structure that overcomes or mitigates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
an aircraft engine low pressure fan last stage bleed air structure comprising:
the gas guiding ring is arranged on the inner side of the inner ring of the final-stage stator;
the inner side of the front end of the gas guiding ring is tightly sealed with the annular boss on the final-stage rotor disk through a castor tooth coating;
the rear end of the gas guiding ring is provided with an inward annular folded edge, and the annular folded edge is connected to the end face of the front end of the support plate ring in the intermediate case through bolts;
the outer wall of the rear end of the air guiding ring is provided with a plurality of protruding parts distributed along the circumferential direction, the front side of each protruding part is provided with an air guiding hole communicated to the air guiding ring, each protruding part is correspondingly positioned on the front side of one support plate in the intermediate case, and the width of each protruding part is smaller than that of the corresponding support plate.
According to at least one embodiment of the present application, in the last stage bleed air structure of the low pressure fan of an aeroengine, the method further comprises:
and sealing glue is poured between the gas guiding ring and the inner ring of the final-stage stator to form a glue ring.
According to at least one embodiment of the present application, in the last stage bleed air structure of the low-pressure fan of the aeroengine, a small gap a is formed between the inner side of the rear end of the rubber ring and the outer side of the bleed air ring.
According to at least one embodiment of the present application, in the last stage bleed air structure of the low-pressure fan of the aeroengine, a small gap b is formed between the end face of the rear end of the rubber ring and each protruding portion.
Drawings
FIG. 1 is a schematic illustration of a prior art aircraft engine low pressure fan last stage bleed air configuration;
FIG. 2 is a schematic illustration of a final bleed air configuration of a low pressure fan of an aircraft engine provided in an embodiment of the present application;
FIG. 3 is a schematic view of a gas guiding ring provided in an embodiment of the present application;
FIG. 4 is a schematic view in the E-E direction of FIG. 3;
wherein:
1-a gas guiding ring; 2-final stator inner ring; 3-last stage rotor disk; 4-supporting plate rings; 5-supporting plates; 6-glue ring; 7-a supporting seat; 8-final stage stator blades; 9-last stage rotor blade.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
In the aeroengine, low pressure fan receiver rear end and intermediary receiver front end butt joint set up extension board ring 4 in the intermediary receiver front end, be provided with a plurality of extension boards 5 along circumference range in intermediary receiver, extension board ring 4 supports through supporting seat 7, install the bearing in the supporting seat 7, the bearing cup joints in intermediary receiver internal rotation epaxial, based on this, this application provides an aeroengine low pressure fan final stage bleed air structure, the following reference 1 through fig. 4 is made this application and is explained in further detail.
An aircraft engine low pressure fan last stage bleed air structure comprising:
the gas guiding ring 1 is arranged on the inner side of the final-stage stator inner ring 2;
the inner side of the front end of the gas guiding ring 1 is tightly sealed with an annular boss on the final-stage rotor disk 3 through a castor tooth coating;
the rear end of the air guiding ring 1 is provided with an inward annular folded edge, and the annular folded edge is connected to the end face of the front end of the supporting plate ring 4 in the intermediate case through bolts;
the outer wall of the rear end of the air-entraining ring 1 is provided with a plurality of protruding parts distributed along the circumferential direction, the front side of each protruding part is provided with an air-entraining hole communicated into the air-entraining ring 1, each protruding part is correspondingly positioned on the front side of one support plate 5 in the intermediate case, and the width of each protruding part is smaller than that of the corresponding support plate 5.
For the last stage air-entraining structure of the aeroengine low pressure fan disclosed by the embodiment, as can be understood by those skilled in the art, the design is that the air-entraining ring 1 is arranged at the inner side of the last stage stator inner ring 2, the inner side of the front end of the air-entraining ring 1 and the annular boss on the last stage rotor disk 3 are tightly sealed by the castor coating, the rear end of the air-entraining ring 1 is connected to the end face of the front end of the inner support plate ring 4 of the medium case by bolts through the inward annular folded edge, so that the front end of the air-entraining ring 1 is tightly sealed, the rear end is fixed, the outer wall of the rear end of the air-entraining ring 1 is designed to have a plurality of protruding parts distributed along the circumferential direction, the front side of each protruding part is provided with air-entraining holes communicated into the air-entraining ring 1, during operation, part of air flow of the main flow of the low pressure fan is introduced into the fan disk shaft through each air-entraining hole, and then is led out to the root of the fan rotor blade by the fan through the hole on the fan disk shaft, and flows back to the passage through the gap of the root of the fan rotor blade, thus realizing the adjustment of the low pressure axial force, and the air-entraining ring 1 can be prevented from leaking into the axial direction of the air-entraining ring 1 from the air-entraining ring 1 to the inner side of the last stage rotor disk to the inner side of the air ring 1.
For the final bleed structure of the low-pressure fan of the aero-engine disclosed in the above embodiment, it will be understood by those skilled in the art that each protruding portion is located on the front side of one support plate 5 in the intermediate casing, and is smaller in width than the width of the corresponding support plate 5, so as to affect the flow of the main flow passage of the low-pressure fan into the flow passage of the intermediate casing, thereby ensuring the overall performance of the aero-engine.
For the final stage bleed air structure of the low pressure fan of the aeroengine disclosed in the above embodiment, it can be understood by those skilled in the art that the annular flange of the inner direction of the bleed air ring 1 is connected to the front end surface of the front end of the support plate ring 4 in the intermediate case by bolts, specifically, the annular flange and the support seat 7 can be designed to be connected to the front end surface of the front end of the support plate ring 4 in the intermediate case by bolts, the connection part on the support seat 7 is located between the annular flange and the support plate ring 4, the support seat 7 is matched and positioned with the front end spigot of the support plate ring 4, the annular flange is matched and positioned with the front end spigot of the support seat 7, and a small gap c is formed between the annular flange and the front end surface of the support plate ring 4, so as to ensure that no constraint and collision and grinding are avoided.
In some alternative embodiments, the final bleed air structure of the low-pressure fan of the aeroengine further comprises:
sealing glue is poured between the air guide ring 1 and the inner ring 2 of the final-stage stator to form a glue ring 6, so that the fixation between the inner ring 2 of the final-stage stator and the final-stage stator blades 8 can be enhanced, the sealing between the air guide ring 1 and the inner ring 2 of the final-stage stator is ensured, and vibration reduction can be carried out between the air guide ring 1 and the inner ring 2 of the final-stage stator.
In some alternative embodiments, in the last stage bleed air structure of the low-pressure fan of the aeroengine, a small gap a is formed between the inner side of the rear end of the rubber ring 6 and the outer side of the bleed air ring 1, so as to have a damping and vibration-reducing function.
In some alternative embodiments, in the last stage bleed air structure of the low-pressure fan of the aeroengine, a small gap b is formed between the end face of the rear end of the rubber ring 6 and each protruding part, so as to avoid collision and grinding.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (4)
1. An aircraft engine low pressure fan last stage bleed air structure comprising:
the gas guiding ring (1) is arranged on the inner side of the final-stage stator inner ring (2);
the inner side of the front end of the gas guiding ring (1) is tightly sealed with an annular boss on the final-stage rotor disk (3) through a castor coating;
the rear end of the gas guiding ring (1) is provided with an inward annular folded edge, and the annular folded edge is connected to the end surface of the front end of the supporting plate ring (4) in the intermediate case through bolts;
the outer wall of the rear end of the air guiding ring (1) is provided with a plurality of protruding parts distributed along the circumferential direction, the front side of each protruding part is provided with an air guiding hole communicated into the air guiding ring (1), each protruding part is correspondingly positioned on the front side of one support plate (5) in the intermediate case, and the width of each protruding part is smaller than the width of the corresponding support plate (5).
2. The aircraft engine low pressure fan last bleed air structure of claim 1, wherein,
further comprises:
and sealing glue is poured between the gas guiding ring (1) and the final-stage stator inner ring (2) to form a glue ring (6).
3. The aircraft engine low pressure fan last bleed air structure of claim 2, wherein,
a small gap a is arranged between the inner side of the rear end of the rubber ring (6) and the outer side of the air entraining ring (1).
4. The aircraft engine low pressure fan last bleed air structure of claim 2, wherein,
the end face of the rear end of the rubber ring (6) and each protruding part are provided with a small gap b.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310105986.8A CN116085073A (en) | 2023-02-13 | 2023-02-13 | Final stage air-entraining structure of low-pressure fan of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310105986.8A CN116085073A (en) | 2023-02-13 | 2023-02-13 | Final stage air-entraining structure of low-pressure fan of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116085073A true CN116085073A (en) | 2023-05-09 |
Family
ID=86199054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310105986.8A Pending CN116085073A (en) | 2023-02-13 | 2023-02-13 | Final stage air-entraining structure of low-pressure fan of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116085073A (en) |
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2023
- 2023-02-13 CN CN202310105986.8A patent/CN116085073A/en active Pending
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