CN114754022A - High-pressure centrifugal compressed air impeller of aircraft engine - Google Patents
High-pressure centrifugal compressed air impeller of aircraft engine Download PDFInfo
- Publication number
- CN114754022A CN114754022A CN202210596642.7A CN202210596642A CN114754022A CN 114754022 A CN114754022 A CN 114754022A CN 202210596642 A CN202210596642 A CN 202210596642A CN 114754022 A CN114754022 A CN 114754022A
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- Prior art keywords
- impeller
- hub
- positioning surface
- centrifugal compressor
- guide wheel
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Links
- 230000003139 buffering effect Effects 0.000 claims description 31
- 238000004146 energy storage Methods 0.000 claims description 6
- 230000001914 calming effect Effects 0.000 claims description 4
- 238000005119 centrifugation Methods 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 3
- 239000013585 weight reducing agent Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000005381 potential energy Methods 0.000 description 4
- 238000005266 casting Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000000411 inducer Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- 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
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
- F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
Abstract
The aero-engine high-pressure centrifugal compressed air impeller provided by the embodiment of the invention comprises a hub part, wherein the center of the hub part is provided with an axle hole, the axle hole of the hub part is provided with a first positioning surface and a second positioning surface, the first positioning surface and the second positioning surface are respectively arranged at the front end and the rear end of the axle hole, and one end of the hub part is provided with an end tooth; the air guide wheel part is arranged on the wheel hub part; the centrifugal impeller part is arranged on the wheel hub part, the air guide wheel part is arranged at the front end of the centrifugal impeller part, and the air guide wheel part is used for uniformly introducing air into the centrifugal impeller part; the weight removing part is arranged on the inner wall of the hub part between the first positioning surface and the second positioning surface; the hub part, the air guide wheel part and the centrifugal impeller part adopt an integrated structure. The high-pressure centrifugal compressor impeller of the aero-engine provided by the embodiment of the invention has the advantages of simplicity and convenience in assembly and high assembly precision.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a high-pressure centrifugal compressed air impeller of an aero-engine.
Background
At present, an impeller of a centrifugal compressor of an aircraft engine consists of an air guide wheel and a centrifugal impeller. The air guide wheel is formed by stainless steel fine casting and is positioned at the front part of the centrifugal impeller to uniformly guide air into the centrifugal impeller, and the front edge of the blade is bent towards the rotation direction of the rotor to adapt to the direction of relative speed when air flow enters the rotor. The single-side semi-open centrifugal impeller is formed by adding an aluminum alloy forging machine, and is provided with straight blades with the same number of wind guide impeller blades, and the rear end of a hub is provided with a corresponding lug which is meshed with a shaft to transmit torque. The guide wheel and the centrifugal impeller are respectively provided with three non-uniformly distributed pin holes for ensuring the relative position of the blades. When the existing aircraft engine centrifugal compressor is installed, two impellers are needed to be balanced respectively, and then are assembled through pins, so that the problems of complex assembly steps and low precision exist.
Disclosure of Invention
The invention aims to provide a high-pressure centrifugal compressor impeller of an aircraft engine, which is used for solving the technical problems of high assembly difficulty and complex assembly steps of a traditional aircraft engine centrifugal compressor.
In order to achieve the purpose, the invention adopts the technical scheme that: the utility model provides an aeroengine high pressure centrifugation impeller of calming anger, aeroengine high pressure centrifugation impeller of calming anger includes:
the hub comprises a hub part, a first positioning surface and a second positioning surface, wherein an axle hole is formed in the center of the hub part, the axle hole of the hub part is provided with the first positioning surface and the second positioning surface, the first positioning surface and the second positioning surface are respectively arranged at the front end and the rear end of the axle hole, and one end of the hub part is provided with an end tooth;
the air guide wheel part is arranged on the wheel hub part;
the centrifugal impeller part is arranged on the hub part, the air guide wheel part is arranged at the front end of the centrifugal impeller part, and the air guide wheel part is used for uniformly introducing air into the centrifugal impeller part;
a weight removing portion provided on the hub portion inner wall between the first positioning surface and the second positioning surface;
the hub part, the air guide wheel part and the centrifugal impeller part adopt an integrated structure.
In one embodiment, the weight removing portion is an arc-shaped groove disposed inside the hub portion.
In one embodiment, the depth of the arc-shaped groove is b, the radius of the arc surface where the first positioning surface is located is a, and b is 2 a-17.
In one embodiment, the blade profile of the air guide wheel part is manufactured in an machining mode.
In one embodiment, the high-pressure centrifugal compressor impeller of the aircraft engine further comprises a buffer part, the buffer part is arranged in the arc-shaped groove, and two sides of the buffer part are respectively connected with two sides of the arc-shaped groove.
In one embodiment, the bottom of the buffer part is provided with a third positioning surface, and the third positioning surface is flush with the second positioning surface.
In one embodiment, the buffer portion is provided with a vent hole.
In one embodiment, the buffering portion comprises a first buffering block, a second buffering block and a buffering ring, one end of the first buffering block is fixed on one side of the arc-shaped groove, one end of the second buffering block is fixed on the other side of the arc-shaped groove, a wedge-shaped groove is arranged on the inner side of the adjacent surface of the first buffering block and the second buffering block, the outer side surface of the buffering ring is in sliding fit in the wedge-shaped groove, and the inner side surface of the buffering ring is in fit on the rotating shaft.
In one embodiment, the buffer part further comprises a connecting rod, one end of the connecting rod is connected with the top of the arc-shaped groove, and the other end of the connecting rod is connected with the buffer ring.
In one embodiment, the buffer portion comprises a curved surface portion and a connecting ring, one end of the connecting ring is fixed on the weight removing portion, the other end of the connecting ring is connected with the curved surface portion, the connecting ring is uniformly arranged between the curved surface portion and the weight removing portion, the curved surface portion is similar to the weight removing portion in shape, and a plurality of energy storage chambers are formed among the curved surface portion, the connecting ring and the weight removing portion.
One or more technical solutions described above in the embodiments of the present invention have at least the following technical effects or advantages:
according to the high-pressure centrifugal compressor impeller of the aircraft engine, the hub part, the air guide wheel part and the centrifugal impeller part are integrated, pin assembly between the two impellers is omitted, static balance is only needed to be performed once during assembly, concentricity and relative position errors of blades are avoided due to integral forming, assembly precision is improved, assembly difficulty is reduced, and assembly steps are simplified. The weight of the high-pressure centrifugal compressor impeller of the aircraft engine is reduced by arranging the weight removing part.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a high-pressure centrifugal compressor impeller of an aircraft engine according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a buffer portion according to an embodiment of the present invention;
fig. 3, 4 and 5 are schematic structural views of a buffer portion according to other embodiments of the present invention;
wherein the respective reference numerals are as follows:
1. a hub portion; 2. an air guide wheel part; 3. a centrifugal impeller portion; 4. a de-weight part; 5. a buffer section; 11. a first positioning surface; 12. a second positioning surface; 13. an end tooth; 51. a third positioning surface; 52. a vent hole; 53. a first buffer block; 54. a second buffer block; 55. a buffer ring; 56. a connecting rod; 57. a curved surface portion; 58. a connecting ring; 59. an energy storage chamber.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
Referring to fig. 1 to 3, an embodiment of the present invention provides a high-pressure centrifugal compressor impeller of an aircraft engine, including a hub portion 1, an air guide wheel portion 2, a centrifugal impeller portion 3, and a weight removal portion 4. The center of the hub portion 1 is provided with an axle hole, the axle hole of the hub portion 1 is provided with a first positioning surface 11 and a second positioning surface 12, the first positioning surface 11 and the second positioning surface 12 are respectively arranged at the front end and the rear end of the axle hole, and one end of the hub portion 1 is provided with an end tooth 13. The air guide wheel portion 2 is provided on the hub portion 1. The centrifugal impeller portion 3 is provided on the hub portion 1, the air guide impeller portion 2 is provided at the front end of the centrifugal impeller portion 3, and the air guide impeller portion 2 is used to uniformly introduce air into the centrifugal impeller portion 3. The weight removing part 4 is disposed on the inner wall of the hub part 1 between the first positioning surface 11 and the second positioning surface 12. The hub unit 1, the air guide wheel unit 2, and the centrifugal impeller unit 3 are integrally formed. The aero-engine high-pressure centrifugal air compressing impeller provided by the embodiment is integrated by setting the hub part 1, the air guide wheel part 2 and the centrifugal impeller part 3, pin assembling between two impellers is cancelled, only one static balance is needed during assembling, and the concentricity and the relative position error of blades are avoided by integral forming, so that the assembling precision is improved, the assembling difficulty is reduced, and the assembling steps are simplified. The weight of the high-pressure centrifugal compressor impeller of the aircraft engine is reduced by arranging the weight removing part 4.
Aiming at the problems of the existing centrifugal compressor, the technical scheme adopted by the embodiment is as follows: on the premise that the profile and the installation scheme of the blade are not changed, titanium alloy is selected as the material of the centrifugal compressor to carry out structural design. And the quality of the rotor is unchanged before and after modification, and the air guide wheel and the centrifugal impeller are integrally processed. The weight removing part 4 is arranged on the inner wall of the hub part 1 between the thicker first positioning surface 11 and the thicker second positioning surface 12, so that the weight removing part 4 can achieve the purpose of weight removal, and the integral strength of the centrifugal compressor cannot be greatly influenced. In one embodiment, the weight removing portion 4 is an arc-shaped groove provided inside the hub portion 1. Compared with a non-arc-shaped groove (such as a square groove) and the like, the weight removing part 4 of the arc-shaped groove has the advantage of smooth transition of a weight removing surface, so that when the centrifugal compressor is stressed, stress concentration is not easy to occur on the weight removing part 4 of the centrifugal compressor, and further the influence of the weight removing part 4 on the overall strength of the centrifugal compressor is further reduced.
In one embodiment, the depth of the arc-shaped groove is b, the radius of the arc surface where the first positioning surface 11 is located is a, and b is 2 a-17. For centrifugal compressors of different sizes, the size of the weight removing part 4 of the centrifugal compressor should be changed correspondingly, so that the centrifugal compressor is ensured to be lighter while the overall strength of the centrifugal compressor is not influenced transitionally. For this reason, the present embodiment optimizes the size of the weight reduction part 4 by limiting the relationship between a and b to b 2a to 17, and when b <2a to 17, the weight reduction effect is not good and the optimal weight reduction cannot be achieved. When b is greater than 2a-17, the weight removing part 4 is too much, so that the thickness of the hub part 1 above the weight removing part 4 is too thin, and although a better weight removing effect can be achieved, the strength of the centrifugal compressor can be seriously influenced, and the centrifugal compressor is easy to deform and fail. Therefore, the size b of the weight removing part 4 is limited to 2a-17, so that the weight removing part 4 can be changed according to centrifugal compressors with different sizes, and the weight of the centrifugal compressor is reduced to the maximum extent while the sufficient strength of the centrifugal compressor is ensured.
In one embodiment, the blade profile of the inducer is machined. Compared with the traditional air guide wheel blade profile adopting casting, the precision of the blade can be improved by adopting a machining mode, and the defects (such as shrinkage porosity, shrinkage holes and the like) of a casting part are avoided, so that the safety coefficient of the blade of the air guide wheel is higher.
Referring to fig. 2, in an embodiment, the high-pressure centrifugal compressor impeller of the aircraft engine further includes a buffer portion 5, the buffer portion 5 is disposed in the arc-shaped groove, and two sides of the buffer portion 5 are respectively connected to two sides of the arc-shaped groove. Through setting up buffer 5 for when centrifugal compressor high-speed rotatory, the stress that the blade of arc recess both sides received can cross buffer 5 and conduct, on the prerequisite that removes the weight effect to heavy part 4 and influence less, improves centrifugal compressor's intensity by a wide margin, offsets the influence of heavy part 4 to centrifugal compressor intensity by a wide margin.
Specifically, the buffer portion 5 is a circular ring with an arc-shaped side surface, two bottom surfaces of the circular ring are respectively connected to the arc-shaped grooves of the weight removing portion 4, and the bending direction of the buffer portion 5 is opposite to the bending direction of the arc-shaped grooves. When the blades give stress to the arc-shaped grooves, the arc-shaped grooves transmit the stress to the buffering portion 5, the buffering portion 5 deforms slightly, the middle position of the buffering portion 5 bends towards the direction of the rotating shaft, the stress is transmitted to the main shaft, the stress is transferred to the main shaft in time, and the risk that the centrifugal compressor deforms due to stress is reduced.
In one embodiment, the bottom of the cushioning portion 5 is provided with a third positioning surface 51, and the third positioning surface 51 is flush with the second positioning surface 12. By arranging the third positioning surface 51, when the centrifugal compressor and the main shaft are assembled, the assembling error of the centrifugal compressor and the main shaft is reduced, and the assembling precision is improved.
In one embodiment, the cushioning portion 5 is provided with a vent hole 52. Through setting up air vent 52 for when the cavity volume that buffer 5 and the arc recess of removing heavy part 4 formed changes, the gas in the cavity can circulate in time, carries out the deformation in order to cooperate buffer 5.
Referring to fig. 3, in an embodiment, the buffering portion 5 includes a first buffering block 53, a second buffering block 54, and a buffering ring 55, one end of the first buffering block 53 is fixed to one side of the arc-shaped groove, one end of the second buffering block 54 is fixed to the other side of the arc-shaped groove, a wedge-shaped groove is disposed on an inner side of an adjacent surface of the first buffering block 53 and the second buffering block 54, an outer side surface of the buffering ring 55 is slidably fitted in the wedge-shaped groove, and an inner side surface of the buffering ring 55 is fitted on the rotating shaft. When the blades on the centrifugal compressor are stressed (mainly the force along the axial direction of the main shaft), the blades transmit the stress to the hub connected with the blades, the hub transmits the stress to the buffer block, so that the buffer block has the tendency of moving towards the middle part, the stress is converted into the pressure towards the center of a circle of the buffer ring 55 through the wedge-shaped groove under the matching of the other buffer block, the buffer ring 55 transmits the pressure to the main shaft, and the stress borne by the blades can be timely transmitted to the main shaft so as to protect the centrifugal compressor.
Referring to fig. 4, in another embodiment, the buffer portion 5 further includes a connecting rod 56, one end of the connecting rod 56 is connected to the top of the arc groove, and the other end of the connecting rod 56 is connected to the buffer ring 55. By connecting the connecting rod 56 to the buffer ring 55, when the impeller rotates, the centrifugal force generated when the air guide wheel part 2 and the centrifugal impeller part 3 rotate can be transferred to the buffer ring 55 through the connecting rod 56, and further the centrifugal force applied to the air guide wheel part 2 and the centrifugal impeller part 3 is transferred to the main shaft, so that the maximum value of the centrifugal force that the air guide wheel part 2 and the centrifugal impeller part 3 can bear is increased, and the upper limit of the impeller rotation speed is increased. In addition, a stable triangular structure is formed between the first/second buffer blocks 53/54 and the buffer ring 55, the connecting rod 56 and the inner surface of the weight removing part 4, so that when the impeller rotates at a high speed, when the wind guide wheel part 2 and the centrifugal impeller part 3 are subjected to a strong centrifugal force, the entire weight reduction part 4, the wind guide wheel part 2 and the centrifugal impeller part 3 tend to be long in the direction of the centrifugal force, and the wind guide wheel part 2 and the centrifugal impeller part 3 tend to extend in the radial direction of the main shaft, so that the weight reduction part 4 tends to be narrow in width and high in height, since the cushion ring 55 is fitted in the wedge grooves of the first and second cushion blocks 53 and 54, therefore, this tendency causes the first and second cushion blocks 53 and 54 to be pressed toward the cushion ring 55, the cushion ring 55 receives a force in the axial direction of the spindle, and the force acts on the connecting rod 56 connected thereto. Because the connecting rod 56 is also subjected to a centrifugal force in a direction perpendicularly outward from the main shaft axis, which is given by the air guide wheel part 2 and the centrifugal impeller part 3, the force given by the buffer ring 55 to the connecting rod 56 is opposite to the centrifugal force given by the air guide wheel part 2 and the centrifugal impeller part 3 to the connecting rod 56, and the two forces are mutually offset, so that the structure of the impeller is more stable and the phenomenon of deformation and the like is not easy to occur during high-speed rotation.
In one embodiment, the cushioning portion 5 includes a curved surface portion 57 and a connecting ring 58, one end of the connecting ring 58 is fixed to the weight removing portion 4, the other end of the connecting ring 58 is connected to the curved surface portion 57, the connecting ring 58 is uniformly disposed between the curved surface portion 57 and the weight removing portion 4, the curved surface portion 57 has a similar shape to the weight removing portion 4, and a plurality of energy storing chambers 59 are formed among the curved surface portion 57, the connecting ring 58 and the weight removing portion 4. By adopting the curved surface part 57, the connecting ring 58 and the weight removing part 4 to form the plurality of independent energy storage chambers 59, when the wind guide wheel part 2 and the centrifugal impeller part 3 have deformation potential energy (when the impeller rotates at high speed, centrifugal force is generated, and further the wind guide wheel part 2 and the centrifugal impeller part 3 have deformation potential energy), the energy storage chambers 59 on the buffer part 5 can provide the wind guide wheel part 2 and the centrifugal impeller part 3 with a force for resisting deformation, and simultaneously transfer part of the deformation potential energy into each energy storage chamber 59, so that the deformation potential energy of the wind guide wheel part 2 and the centrifugal impeller part 3 is reduced, and further the probability of deformation of the wind guide wheel part 2 and the centrifugal impeller part 3 is reduced. In addition, because the curved surface part 57 and the weight-removing part 4 are similar in structure, the distance between the curved surface part 57 and the weight-removing part 4 is basically consistent, so that the force of the buffer part 5 for giving the resistance to the weight-removing part 4 is more uniform, and the phenomenon that some positions of the weight-removing part 4 are deformed due to overlarge centrifugal force and even cracked and damaged is avoided.
In addition, when the buffer portion 5 is manufactured, the connection ring 58 of the weight reduction portion 4 and the impeller main body may be integrally cast, and then the curved surface portion 57 may be divided into a plurality of portions, which are welded to the connection ring 58 in stages.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an aeroengine high pressure centrifugation impeller of calming anger, its characterized in that, aeroengine high pressure centrifugation impeller of calming anger includes:
the hub comprises a hub part, a first positioning surface and a second positioning surface, wherein an axle hole is formed in the center of the hub part, the axle hole of the hub part is provided with the first positioning surface and the second positioning surface, the first positioning surface and the second positioning surface are respectively arranged at the front end and the rear end of the axle hole, and one end of the hub part is provided with an end tooth;
the air guide wheel part is arranged on the wheel hub part;
the centrifugal impeller part is arranged on the hub part, the air guide wheel part is arranged at the front end of the centrifugal impeller part, and the air guide wheel part is used for uniformly introducing air into the centrifugal impeller part;
a weight removing portion provided on the hub portion inner wall between the first positioning surface and the second positioning surface;
the hub part, the air guide wheel part and the centrifugal impeller part adopt an integrated structure.
2. The high-pressure centrifugal compressor impeller of the aircraft engine according to claim 1, characterized in that:
the weight removing part is an arc-shaped groove arranged inside the hub part.
3. The high-pressure centrifugal compressor impeller of the aircraft engine as claimed in claim 2, wherein:
the depth of the arc-shaped groove is b, the radius of the arc surface where the first positioning surface is located is a, and b is 2 a-17.
4. The aero-engine high-pressure centrifugal compressor impeller as claimed in claim 1, wherein:
the blade profile of the air guide wheel part is manufactured in a machining mode.
5. The high-pressure centrifugal compressor impeller of the aircraft engine as claimed in claim 2, wherein:
the high-pressure centrifugal compressed air impeller of the aircraft engine further comprises a buffering part, wherein the buffering part is arranged in the arc-shaped groove, and two sides of the buffering part are respectively connected with two sides of the arc-shaped groove.
6. The high-pressure centrifugal compressor impeller of the aircraft engine as claimed in claim 5, wherein:
the bottom of buffering portion is provided with the third locating surface, the third locating surface with the second locating surface parallel and level.
7. The high-pressure centrifugal compressor impeller of the aircraft engine as claimed in claim 5, wherein:
the buffer part is provided with a vent hole.
8. The aero-engine high-pressure centrifugal compressor impeller as claimed in claim 5, wherein:
buffering portion includes first buffer block, second buffer block, buffering ring, first buffer block one end is fixed in one side of arc recess, the one end of second buffer block is fixed in the opposite side of arc recess, first buffer block with the inboard of second buffer block looks proximal surface is provided with the wedge groove, the lateral surface sliding fit of buffering ring in the wedge inslot, just the medial surface cooperation of buffering ring is in the pivot.
9. The aero-engine high-pressure centrifugal compressor impeller as claimed in claim 8, wherein:
the buffer part further comprises a connecting rod, one end of the connecting rod is connected with the top of the arc-shaped groove, and the other end of the connecting rod is connected with the buffer ring.
10. The high-pressure centrifugal compressor impeller of the aircraft engine as claimed in claim 5, wherein:
the buffer part comprises a curved surface part and a connecting ring, one end of the connecting ring is fixed on the weight removing part, the other end of the connecting ring is connected with the curved surface part, the connecting ring is uniformly arranged between the curved surface part and the weight removing part, the shape of the curved surface part is similar to that of the weight removing part, and a plurality of energy storage chambers are formed among the curved surface part, the connecting ring and the weight removing part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210596642.7A CN114754022B (en) | 2022-05-30 | 2022-05-30 | High-pressure centrifugal compressed air impeller of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210596642.7A CN114754022B (en) | 2022-05-30 | 2022-05-30 | High-pressure centrifugal compressed air impeller of aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114754022A true CN114754022A (en) | 2022-07-15 |
| CN114754022B CN114754022B (en) | 2022-12-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210596642.7A Active CN114754022B (en) | 2022-05-30 | 2022-05-30 | High-pressure centrifugal compressed air impeller of aircraft engine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101149061A (en) * | 2007-07-30 | 2008-03-26 | 北京航空航天大学 | Centrifugal impeller suitable for high rotation speed operation |
| CN103967837A (en) * | 2014-05-09 | 2014-08-06 | 中国航空动力机械研究所 | Compressor centrifugal vane wheel of aircraft engine |
| US20150267543A1 (en) * | 2014-03-20 | 2015-09-24 | Cameron International Corporation | Monolithic shrouded impeller |
| CN106989056A (en) * | 2017-06-01 | 2017-07-28 | 中国航发湖南动力机械研究所 | centrifugal impeller and compressor |
| CN109209512A (en) * | 2018-10-19 | 2019-01-15 | 中国航发湖南动力机械研究所 | Engine, wheeling disk structure and preparation method thereof |
-
2022
- 2022-05-30 CN CN202210596642.7A patent/CN114754022B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101149061A (en) * | 2007-07-30 | 2008-03-26 | 北京航空航天大学 | Centrifugal impeller suitable for high rotation speed operation |
| US20150267543A1 (en) * | 2014-03-20 | 2015-09-24 | Cameron International Corporation | Monolithic shrouded impeller |
| CN103967837A (en) * | 2014-05-09 | 2014-08-06 | 中国航空动力机械研究所 | Compressor centrifugal vane wheel of aircraft engine |
| CN106989056A (en) * | 2017-06-01 | 2017-07-28 | 中国航发湖南动力机械研究所 | centrifugal impeller and compressor |
| CN109209512A (en) * | 2018-10-19 | 2019-01-15 | 中国航发湖南动力机械研究所 | Engine, wheeling disk structure and preparation method thereof |
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| Publication number | Publication date |
|---|---|
| CN114754022B (en) | 2022-12-30 |
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Inventor after: Liu Zhichao Inventor after: Yuan Yueyang Inventor after: Niu Jichao Inventor after: Liu Chen Inventor after: Zhao Yu Inventor after: Pan Ningmin Inventor after: Tang Huaiyuan Inventor after: Zhang Zezhen Inventor after: Ji Jiangfeng Inventor after: Tong Yongxiang Inventor before: Liu Zhichao Inventor before: Yuan Yue Inventor before: Niu Jichao Inventor before: Liu Chen Inventor before: Zhao Yu Inventor before: Pan Ningmin Inventor before: Tang Huaiyuan Inventor before: Zhang Zezhen Inventor before: Ji Jiangfeng Inventor before: Tong Yongxiang |
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Denomination of invention: A high-pressure centrifugal compressor impeller for aircraft engines Granted publication date: 20221230 Pledgee: CITIC Bank Nanchang branch of Limited by Share Ltd. Pledgor: Jiangxi Zhongfa Tianxin Aero Engine Technology Co.,Ltd. Registration number: Y2024980008468 |
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