CN117514465A - Air inlet cone and aeroengine comprising same - Google Patents
Air inlet cone and aeroengine comprising same Download PDFInfo
- Publication number
- CN117514465A CN117514465A CN202210883589.9A CN202210883589A CN117514465A CN 117514465 A CN117514465 A CN 117514465A CN 202210883589 A CN202210883589 A CN 202210883589A CN 117514465 A CN117514465 A CN 117514465A
- Authority
- CN
- China
- Prior art keywords
- wall
- air
- cone
- nose cone
- holes
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007704 transition Effects 0.000 claims description 14
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000005452 bending Methods 0.000 claims 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 15
- 239000007788 liquid Substances 0.000 abstract description 6
- 230000000694 effects Effects 0.000 description 9
- 238000010438 heat treatment Methods 0.000 description 9
- 238000007710 freezing Methods 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000008014 freezing Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
- B64C11/14—Spinners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an air inlet cone and an aeroengine comprising the same, wherein the air inlet cone comprises a main body and a nose cone part, the main body comprises an outer wall, the nose cone part is connected with the end part of the outer wall, the outer side surface of the nose cone part is provided with a first outline, the outer side surface of the outer wall is provided with a second outline, and the second outline is bent and contracted towards the axis direction of the main body in the direction away from the first outline. The cold air flows along the outer wall of the nose cone part, the outer side of the outer wall bends and contracts towards the axis direction of the main body in the direction away from the first contour, the inertia of liquid water drops in the air is far greater than that of the air, the water drops are difficult to bend like the air, the streamline impacts the second contour, and the air drops linearly move along the direction of the first contour, namely, the outer wall of the air inlet cone is difficult to generate icing, and the engine efficiency is improved.
Description
Technical Field
The invention belongs to the technical field of anti-freezing of aircraft engine hoods, and particularly relates to an air inlet cone and an aircraft engine comprising the same.
Background
During flight, aircraft engines are exposed to low temperatures, which can lead to icing of surfaces. However, the icing can seriously affect the flight safety, especially for an aeroengine, once the icing occurs, the air inlet of the engine is blocked due to light weight, and the working efficiency of the engine is reduced; the heavy ice falling off in a large area can cause mechanical damage to an air inlet system of the engine, so that the engine is flameout, and serious safety accidents are caused. The front section wall and the rear section wall of the existing air inlet cone are positioned on the same plane, and cold air easily forms ice crystals at the surface of the rear section wall to cause icing.
Disclosure of Invention
The invention aims to overcome the defect that the rear end of an air inlet cone is easy to generate icing in the prior art, and provides the air inlet cone and an aeroengine comprising the air inlet cone.
The invention solves the technical problems by the following technical scheme:
an air inlet cone, the air inlet cone includes main part and nose cone portion, the main part includes the outer wall, nose cone portion with the tip of outer wall is connected, the outside surface of nose cone portion has first profile, the outside surface of outer wall has the second profile, the second profile is in keeping away from the direction of first profile towards the crooked shrink of axis direction of main part.
In this scheme, cold air flows along the lateral surface of nose cone towards the outer wall of rear, because the lateral surface (i.e. second outline) of outer wall is in the direction of keeping away from first outline the crooked shrink of axis direction towards the main part, the liquid water droplet inertia in the air is greater than the air far away, the water droplet is difficult to buckle the streamline and strike second outline like the air, but along the direction rectilinear motion of first outline, the phenomenon of icing is difficult to take place for the air inlet cone outer wall promptly, has improved engine efficiency.
Preferably, the second contour is smoothly tangent to the first contour.
In this scheme, the lateral surface of nose cone portion is tangent with the lateral surface of outer wall is smooth, and when air flowed through along the intake cone surface, the resistance that receives was less, and engine efficiency is higher.
Preferably, the main body further comprises an inner wall, the inner wall is arranged at the end part of the outer wall, the inner wall is provided with a through hole, the nose cone portion is sleeved outside the inner wall in a clearance mode to form an air flow channel, and the nose cone portion is provided with an air hole.
The inner wall is provided with the through hole, and nose cone portion clearance cover is established in the outside of inner wall, and through this structural style, the air current passageway is linked together with the inside of inner wall, and the through hole can be with the leading-in air current passageway of compressor to heat nose cone portion, prevent that nose cone portion from producing and freezing. The nose cone part is also provided with air holes, hot air in the air flow channel can flow to the outer side of the nose cone part through the air holes to neutralize external cold air, and further the nose cone part is prevented from being frozen. Meanwhile, the hot air flowing to the outside flows to the outer side surface of the outer wall under the action of the air flow, and the hot air is heated to prevent the outer side surface of the outer wall from icing.
Preferably, the inner wall is conical, the conical tip of the inner wall faces the nose cone, and the through hole is formed in the conical tip of the inner wall.
By adopting the structure, the airflow channel between the nose cone part and the inner wall is narrower, the through hole can be close to the nose cone part as much as possible, the hot air is prevented from dissipating heat in the airflow channel, and the heating effect of the hot air on the nose cone part is better.
Preferably, the number of the through holes is more than 2.
The number of through holes is more than 2, so that the hot air spraying range can be enlarged, and the heating effect on the nose cone part can be further improved.
Preferably, the plurality of through holes are uniformly distributed on the conical tip part of the inner wall at equal intervals.
The taper points of the through holes on the inner wall are uniformly arranged at equal intervals, so that hot air injection is more uniform, and icing caused by the fact that a certain area of the nose cone is not heated by hot air is prevented.
Preferably, the air hole is arranged at the end part of the nose cone part, which is close to the outer wall.
The air hole is arranged at one end of the nose cone part close to the outer wall, so that hot air can flow to the outer surface of the outer wall immediately after flowing out of the air flow channel, and the heat loss and the reduction of the heating effect on the outer wall after the hot air stays outside for a long time are prevented. In addition, because the through hole is arranged at the cone tip of the inner wall, the flowing path of the hot air in the air flow channel is longer, and the heating effect of the nose cone part is also improved.
Preferably, the number of the air holes is a plurality, and the plurality of the air holes are uniformly distributed along the circumferential direction of the nose cone part.
By adopting the structural form, the direction of hot air flowing from the airflow channel to the outside is uniform, the outer wall can be heated more comprehensively, and the local ice formation of the outer wall is prevented.
Preferably, the main body further comprises a transition section, the inner wall is connected with the outer wall through the transition section, and an included angle between the transition section and an axial extension line of the air inlet cone is an acute angle.
The changeover portion is that the slope upwards links to each other with the outer wall, and when hot air flowed outside from the air current passageway, the gas pocket was flowed out along the changeover portion, and the resistance that receives when hot air was flowed out on the one hand is less, and on the other hand, the direction slope of hot air outflow was to the outer wall, avoids hot air to blow out perpendicularly upwards and can't contact with the outer wall and lead to the heat extravagant.
Preferably, the air hole is an inclined hole, and the inclination angle of the inclined hole is the same as that of the transition section.
The resistance that hot air received along changeover portion outflow gas pocket is less, and the directionality is stronger.
An aeroengine comprising an air intake cone as described above.
The cold air flows along the outer wall of the nose cone part of the aeroengine air inlet cone, the outer side surface (namely the second outline) of the outer wall bends and contracts towards the axis direction of the main body in the direction away from the first outline, the inertia of liquid water drops in the air is far greater than that of the air, the water drops are difficult to bend like the air, the streamline impacts the second outline, and the water drops linearly move along the direction of the first outline, namely the outer wall of the air inlet cone is difficult to generate icing phenomenon, and the engine efficiency is improved.
The invention has the positive progress effects that: the cold air flows along the outer wall of the nose cone part, the outer side (namely the second outline) of the outer wall bends and contracts towards the axis direction of the main body in the direction away from the first outline, the inertia of liquid water drops in the air is far greater than that of the air, the water drops are difficult to bend and flow lines like the air to strike the second outline, and the water drops move linearly along the direction of the first outline, namely the outer wall of the air inlet cone is difficult to generate icing, and the engine efficiency is improved.
Drawings
FIG. 1 is a schematic view of an air intake cone according to an embodiment of the present invention.
FIG. 2 is a schematic view of another embodiment of an intake cone according to the present invention.
Fig. 3 is a schematic view of another structure of an air intake cone according to an embodiment of the present invention.
Fig. 4 is a schematic view of the structure of the inner wall of the air inlet cone of the invention.
Description of the reference numerals
Nose cone 1
Air holes 11
Body 2
Outer wall 21
Inner wall 22
Through hole 221
Air flow channel 3
Transition section 23
First contour line 3
Second contour 4
Detailed Description
The invention is further illustrated by means of the following examples, which are not intended to limit the scope of the invention.
Referring to fig. 1 to 3, the present embodiment provides an air intake cone including a main body 2 and a nose cone portion 1, the main body 2 including an outer wall 21, the nose cone portion 1 being connected to an end portion of the outer wall 21, an outer side surface of the nose cone portion 1 having a first outer contour 3, an outer side surface of the outer wall 21 having a second outer contour 4, the second outer contour 4 being curved and contracted in a direction away from the first outer contour 3 toward an axis direction of the main body 2.
In this embodiment, the cool air flows along the outer wall 21 of the nose cone 1, which is directed to the rear, and since the outer side (i.e., the second contour line 4) of the outer wall 21 is curved and contracted in the direction away from the first contour line 3 toward the axis of the main body 2, the inertia of the liquid water drops in the air is far greater than that of the air, and the water drops are difficult to bend and flow into the flow line like the air to strike the second contour line 4, but move linearly along the direction of the first contour line 3, i.e., the air intake cone outer wall 21 is not easy to generate icing phenomenon, thereby improving the engine efficiency.
As shown in fig. 1, as a preferred embodiment, the second contour 4 is smoothly tangent to the first contour 3.
In this embodiment, the outer side surface of the nose cone portion 1 is smoothly tangent to the outer side surface of the outer wall 21, and when air flows along the outer surface of the air intake cone, the resistance is smaller, and the engine efficiency is higher. Of course in other embodiments the nose cone 1 and the outer wall 21 may be connected together by an internal component, i.e. the second profile 4 and the first profile 3 may be provided separately, forming an annular vent channel.
As a preferred embodiment, the main body 2 further includes an inner wall 22, the inner wall 22 is disposed at an end of the outer wall 21, the inner wall 22 is provided with a through hole 221, the nose cone 1 is disposed at an outer side of the inner wall 22 in a clearance fit to form the air flow channel 3 (see fig. 1), and the nose cone 1 is provided with the air hole 11.
The inner wall 22 is provided with a through hole 221, the nose cone 1 is sleeved outside the inner wall 22 in a clearance way, through the structural form, the air flow channel 3 is communicated with the inside of the inner wall 22, and the through hole 221 can guide hot air of a compressor into the air flow channel 3, so that the nose cone 1 is heated, and the nose cone 1 is prevented from icing. The nose cone portion 1 is further provided with an air hole 11, hot air in the air flow channel 3 can flow to the outer side of the nose cone portion 1 through the air hole 11 to neutralize external cold air, and further the nose cone portion 1 is prevented from being frozen. Meanwhile, the hot air flowing to the outside flows to the outer side surface of the outer wall 21 under the action of the air flow, and the heating thereof can also prevent the outer side surface of the outer wall 21 from freezing.
The inner wall 22 is specifically described below, the outer shape of the inner wall 22 is a cone smaller than the nose cone 1 by one number, the cone tip faces the nose cone 1, and the through hole 221 is provided in the cone tip of the inner wall 22.
By adopting the structure, the air flow channel 3 between the nose cone part 1 and the inner wall 22 is narrower, the through hole 221 can be close to the nose cone part 1 as much as possible, the hot air is prevented from dissipating heat in the air flow channel 3, and the heating effect of the hot air on the nose cone part 1 is better. Of course, in other embodiments, the inner wall 22 may be planar, so long as the nose cone 1 and the inner wall 22 form an airflow channel 3 for hot air to enter.
Referring to fig. 4, as a preferred embodiment, the number of the through holes 221 is plural.
The plurality of through holes 221 can increase the range of hot air injection, and further improve the heating effect on the nose cone 1.
As a preferred embodiment, the plurality of through holes 221 are equally spaced at the conical tip of the inner wall 22.
Uniformly arranging the through holes 221 at equal intervals at the cone tip of the inner wall 22 can make the hot air injection more uniform, and prevent icing caused by that a certain area of the nose cone 1 is not heated by the hot air.
As a preferred embodiment, the air holes 11 are provided at the end of the nose cone 1 near the outer wall 21.
The air hole 11 is arranged at one end of the nose cone part 1 close to the outer wall 21, so that hot air can flow to the outer surface of the outer wall 21 immediately after flowing out of the air flow channel 3, and heat dissipation and reduction of the heating effect of the outer wall 21 are prevented after the hot air stays outside for a long time. In addition, since the through hole 221 is provided at the taper point of the inner wall 22, the flow path of the hot air in the air flow passage 3 is long, which is also advantageous for improving the heating effect of the nose cone 1.
As a preferred embodiment, the number of the air holes 11 is plural, and the plurality of air holes 11 are uniformly arranged along the circumferential direction of the nose cone portion 1.
By adopting the structure, the direction of hot air flowing from the air flow channel 3 to the outside is uniform, the outer wall 21 can be heated more comprehensively, and the outer wall 21 is prevented from being frozen locally.
As a preferred embodiment, the body 2 further comprises a transition section 23, the inner wall 22 being connected to the outer wall 21 by means of the transition section 23, the angle between the transition section 23 and the axial extension of the inlet cone being acute.
The changeover portion 23 is the slope and upwards links to each other with outer wall 21, and when hot air flowed outside from air current passageway 3, along changeover portion 23 outflow gas pocket 11, and the resistance that receives when on the one hand hot air flows out is less, and on the other hand, the direction that hot air flows out is to outer wall 21 slope, avoids hot air to blow out perpendicularly upwards and can't contact with outer wall 21 and lead to the heat extravagant.
As a preferred embodiment, the air holes 11 are inclined holes, the inclination angle of which is the same as that of the transition section 23.
The hot air flows out of the air hole 11 along the transition section 23 and has smaller resistance and stronger directivity.
The embodiment also provides an aeroengine, which comprises the air inlet cone.
The cold air flows along the outer wall 21 of the nose cone part 1 of the aeroengine air inlet cone, the outer side surface (namely the second contour line 4) of the outer wall 21 bends and contracts towards the axis direction of the main body 2 in the direction away from the first contour line 3, the inertia of liquid water drops in the air is far greater than that of the air, the water drops are difficult to bend and streamline like the air to strike the second contour line 4, and the water drops linearly move along the direction of the first contour line 3, namely the air inlet cone outer wall 21 is difficult to generate icing phenomenon, and the engine efficiency is improved.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (11)
1. The utility model provides an inlet cone, its characterized in that, inlet cone includes main part and nose cone portion, the main part includes the outer wall, nose cone portion with the tip of outer wall is connected, the outside surface of nose cone portion has first profile, the outside surface of outer wall has the second profile, the second profile is in keeping away from first profile the direction bending shrinkage towards the axis direction of main part.
2. The air intake cone of claim 1, wherein the second profile is smoothly tangent to the first profile.
3. The air intake cone of claim 1, wherein the body further comprises an inner wall disposed at an end of the outer wall, the inner wall being provided with a through hole, the nose cone gap being disposed outside of the inner wall to form an air flow channel, the nose cone being provided with an air hole.
4. The air inlet cone of claim 3, wherein the inner wall is conical, the conical tip of the inner wall faces the nose cone, and the through hole is formed in the conical tip of the inner wall.
5. The air intake cone of claim 4, wherein the number of through holes is 2 or more.
6. The air intake cone of claim 5, wherein a plurality of said through holes are equally spaced at the cone tip of said inner wall.
7. The air intake cone of claim 3, wherein the air holes are provided at an end of the nose cone portion adjacent the outer wall.
8. The air intake cone of claim 7, wherein the number of air holes is plural, and the plural air holes are uniformly arranged along the circumferential direction of the nose cone portion.
9. The intake cone of claim 7, wherein the body further comprises a transition section, the inner wall being connected to the outer wall by the transition section, the transition section being at an acute angle to an axial extension of the intake cone.
10. The air intake cone of claim 9, wherein the air holes are inclined holes having the same inclination angle as the transition section.
11. An aircraft engine, characterized in that it comprises an inlet cone according to any one of claims 1-10.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210883589.9A CN117514465A (en) | 2022-07-26 | 2022-07-26 | Air inlet cone and aeroengine comprising same |
| PCT/CN2023/108972 WO2024022304A1 (en) | 2022-07-26 | 2023-07-24 | Inlet cone and aeroengine comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210883589.9A CN117514465A (en) | 2022-07-26 | 2022-07-26 | Air inlet cone and aeroengine comprising same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117514465A true CN117514465A (en) | 2024-02-06 |
Family
ID=89705484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210883589.9A Pending CN117514465A (en) | 2022-07-26 | 2022-07-26 | Air inlet cone and aeroengine comprising same |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN117514465A (en) |
| WO (1) | WO2024022304A1 (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB885908A (en) * | 1957-08-30 | 1962-01-03 | Bristol Siddeley Engines Ltd | Improvements in intakes for compressible fluids |
| GB9828812D0 (en) * | 1998-12-29 | 1999-02-17 | Rolls Royce Plc | Gas turbine nose cone assembly |
| CN106555675B (en) * | 2015-09-30 | 2018-07-10 | 中国航发商用航空发动机有限责任公司 | Fan inlet cone and aviation turbofan engine gas handling system |
| US11098646B2 (en) * | 2019-07-08 | 2021-08-24 | Pratt & Whitney Canada Corp. | Gas turbine impeller nose cone |
| CN216922297U (en) * | 2022-01-05 | 2022-07-08 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine air inlet cone and aeroengine |
-
2022
- 2022-07-26 CN CN202210883589.9A patent/CN117514465A/en active Pending
-
2023
- 2023-07-24 WO PCT/CN2023/108972 patent/WO2024022304A1/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| WO2024022304A1 (en) | 2024-02-01 |
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