CN112324573A - Aeroengine air inlet cover - Google Patents
Aeroengine air inlet cover Download PDFInfo
- Publication number
- CN112324573A CN112324573A CN202011179125.7A CN202011179125A CN112324573A CN 112324573 A CN112324573 A CN 112324573A CN 202011179125 A CN202011179125 A CN 202011179125A CN 112324573 A CN112324573 A CN 112324573A
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- Prior art keywords
- air inlet
- metal net
- central axis
- mounting
- hood
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- 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
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
- F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
Abstract
The invention discloses an air inlet hood of an aero-engine, which comprises a left half air inlet hood and a right half air inlet hood which are symmetrically arranged, wherein the left half air inlet hood and the right half air inlet hood both comprise: the plane development of the metal net is rectangular, the central axis is bent into an arc shape, and the cross section profiles of the metal net, which are perpendicular to the central axis of the metal net, are bent into the arc shape and have the same size; the mounting edges are symmetrically arranged at the arc-shaped edges of the left side edge and the right side edge of the metal net, are parallel to the central axis and are used for fixing the left side edge and the right side edge of the metal net at the corresponding mounting positions of the air inlet casing; and the mounting frame is fixedly arranged at two ends of the vertical central axis of the metal mesh, the shape of the mounting frame is matched with the cross section profile shape of the metal mesh, and the mounting frame is used for connecting the left half air inlet cover and the right half air inlet cover to form a complete annular aero-engine air inlet cover. The invention has simple structure, easy assembly and small total pressure loss of air inlet, and effectively solves the defect that the single plane air inlet cover is easy to block the air inlet channel under the icing condition.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to an aero-engine air inlet cover.
Background
The air inlet cover is used as a protective net on an air inlet casing of the aero-engine, so that foreign objects (such as sand, stones, branches, birds and the like) can be effectively prevented from entering the engine, the rotating parts of the engine are protected, and the reliable service life of the engine is prolonged. Some air inlet hoods of the existing aircraft engine are simple in structure and are single planes, and air inlet channels of the engine are easily blocked under icing conditions, so that the engine breaks down, and flight safety is influenced; some air inlet covers have complex structures and more parts, and realize the smoothness of an air inlet flow passage under the icing condition through complex structural forms, thereby bringing about the result that the total pressure loss of the inlet air is large.
Disclosure of Invention
The invention provides an air inlet cover of an aero-engine, which aims to solve the technical problems that the existing air inlet cover of the aero-engine is easy to freeze and block, has a complex structure and is large in total pressure loss of air inlet.
The technical scheme adopted by the invention is as follows:
the utility model provides an aeroengine inlet hood, includes half left inlet hood and half right inlet hood that the symmetry set up, half left inlet hood and half right inlet hood all include:
the plane development of the metal net is rectangular, the central axis is bent into an arc shape, and the cross section profiles of the metal net, which are perpendicular to the central axis of the metal net, are bent into the arc shape and have the same size;
the mounting edges are symmetrically arranged at the arc-shaped edges of the left side edge and the right side edge of the metal net, are parallel to the central axis and are used for fixing the left side edge and the right side edge of the metal net at the corresponding mounting positions of the air inlet casing;
and the mounting frame is fixedly arranged at two ends of the vertical central axis of the metal mesh, the shape of the mounting frame is matched with the cross section profile shape of the metal mesh, and the mounting frame is used for connecting the left half air inlet cover and the right half air inlet cover to form a complete annular aero-engine air inlet cover.
Further, the central axis of the metal net is bent into a semicircular shape.
Furthermore, the cross section profiles of the metal nets perpendicular to the central axis of the metal nets are bent into semi-circles and are consistent in size.
Furthermore, the concave side of the mounting edge is provided with a U-shaped open slot along the length direction, and the U-shaped open slot is matched with the arc-shaped flange at the mounting position corresponding to the air inlet casing.
Furthermore, the height of one side, close to the central axis, of the U-shaped open slot is greater than the height of one side, far away from the central axis, of the U-shaped open slot.
Furthermore, the height of one side, close to the central axis, of the U-shaped open slot is 1-2 mm greater than the height of one side, far away from the central axis, of the U-shaped open slot.
Further, the mounting bracket includes:
the mounting rack main body is fixedly arranged at two ends of the metal net vertical central axis and is matched with the cross section outline shape of the metal net in shape;
and the bolt connecting pieces are symmetrically fixed on the mounting frame main body and are provided with through holes for fixing two ends of the metal net at the corresponding mounting positions of the air inlet casing through bolts.
Further, the surface of the metal mesh is provided with a hydrophobic coating, and the contact angle of the hydrophobic coating is greater than 120 degrees.
Furthermore, the metal net fixing device further comprises a reinforcing rib which is attached to the outer side of the metal net, and two ends of the reinforcing rib are fixedly connected with the mounting edges on the left side and the right side of the metal net respectively.
Furthermore, the middle part of the cross section of the metal net, the middle part of the reinforcing rib and the middle part of the mounting rack are provided with yielding planes in the middle.
The invention has the following beneficial effects:
the air inlet cover comprises a metal net, a mounting edge and a mounting frame, wherein the central axis of the metal net is bent into an arc shape, and the cross section profiles of the metal net, which are perpendicular to the central axis of the air inlet cover, are bent into the arc shape and are consistent in size; the mounting edges are symmetrically arranged at the arc-shaped edges of the left side and the right side of the metal net and are parallel to the central axis; the mounting rack is fixedly arranged at two ends of the metal net perpendicular to the central axis. Compared with the prior art, the invention has the advantages that: the structure is simple, the assembly is easy, and the total pressure loss of air inlet is small; and secondly, the design of the convex net cover with the cambered surface is adopted, so that the air inlet flow can be better ensured to still enter the engine from the side surface under the icing condition, the air inlet passage of the engine can not be blocked in a large area, and the defect that the air inlet passage is easy to block by the single-plane air inlet cover under the icing condition is effectively overcome.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic perspective view of an aircraft engine inlet cowl according to a preferred embodiment of the present invention.
Fig. 2 is a front view of a mounting side of a preferred embodiment of the present invention.
Fig. 3 is a schematic sectional view taken along line a-a in fig. 2.
Fig. 4 is a schematic front view of a mount of a preferred embodiment of the invention.
Fig. 5 is a schematic sectional view taken along line a-a in fig. 4.
Fig. 6 is a schematic top view of a mount of the preferred embodiment of the present invention.
Fig. 7 is a schematic front view of a metal mesh according to a preferred embodiment of the present invention.
Fig. 8 is a schematic sectional view taken along line a-a in fig. 7.
FIG. 9 is a schematic view of the mounting of the inlet cowl to the inlet case of the preferred embodiment of the present invention.
In the figure:
1. reinforcing ribs; 2. a metal mesh; 3. installing edges; 4. a mounting frame; 41. a mounting bracket main body; 42. connecting the sheet by bolts; 5. an air intake hood; 6. an air inlet casing; 7. and (4) yielding planes.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1, a preferred embodiment of the present invention provides an air intake cover for an aircraft engine, including a left half air intake cover and a right half air intake cover which are symmetrically arranged, and both the left half air intake cover and the right half air intake cover include:
the plane development of the metal net 2 is rectangular, the central axis is bent into an arc shape, the cross section profiles of the metal net 2 perpendicular to the central axis are bent into arc shapes with the same size, and the metal net 2 is made of 0Cr18Ni 9-5/0.8A;
the mounting edges 3 are symmetrically arranged at the arc-shaped edges of the left side and the right side of the metal mesh 2, are parallel to the central axis and are used for fixing the left side and the right side of the metal mesh 2 at the corresponding mounting positions of the air inlet casing 6, and the material of the mounting edges 3 is 0Cr18Ni10 Ti-0.5;
the mounting bracket 4 is fixedly arranged at two ends of the vertical central axis of the metal mesh 2, the shape of the mounting bracket is matched with the cross section profile shape of the metal mesh 2, the left half air inlet cover and the right half air inlet cover are connected to form a complete annular aero-engine air inlet cover, and the mounting bracket 4 is made of 0Cr18Ni10 Ti-1.0.
The air inlet cover of the embodiment comprises a left half air inlet cover and a right half air inlet cover which are symmetrically arranged, wherein each of the left half air inlet cover and the right half air inlet cover comprises a metal net 2, a mounting edge 3 and a mounting frame 4, the central axis of the metal net 2 is bent into an arc shape, and the cross section profiles of the metal net perpendicular to the central axis are bent into the arc shape and have the same size; the mounting edges 3 are symmetrically arranged at the arc-shaped edges of the left side and the right side of the metal net 2 and are parallel to the central axis; the mounting rack 4 is fixedly arranged at two ends of the metal net 2. Compare prior art, the inlet hood advantage of this embodiment includes: the structure is simple, the assembly is easy, and the total pressure loss of air inlet is small; and secondly, the design of the convex net cover with the cambered surface is adopted, so that the intake airflow can still enter the engine from the side surface of the metal net 2 under the icing condition, the large-area blockage of an engine intake duct is avoided, and the defect that the intake duct is easy to block by the single-plane intake cover under the icing condition is effectively overcome.
In a preferred embodiment of the invention, as shown in fig. 7, the wire netting 2 is curved in a semi-circular shape at its central axis.
In the preferred embodiment of the present invention, each cross-sectional profile of the metal mesh 2 perpendicular to its central axis is curved into a semicircle and uniform in size.
As shown in fig. 2 and 3, in the preferred embodiment of the present invention, the concave side of the mounting edge 3 is provided with a U-shaped open slot along the length direction, and the U-shaped open slot is matched with the arc-shaped flange at the corresponding mounting position of the air inlet casing 6.
In this embodiment, the concave side of installation limit 3 is provided with U type open slot along length direction, and the arc flange phase-match of the installation department that this U type open slot and air inlet machine casket 6 correspond, during the installation, only need to correspond the arc flange of the installation department that U type open slot and air inlet machine casket 6 correspond and be connected during the installation, can with the installation department that air inlet machine casket 6 corresponds is fixed to metal mesh 2 left and right sides limit, convenient and fast.
In a preferred embodiment of the present invention, a height of one side of the U-shaped open slot close to the central axis is greater than a height of one side of the U-shaped open slot far from the central axis.
In this embodiment, the height of the two mounting edges 3 close to the central axis is greater than the height of the two mounting edges 3 away from the central axis, the raised portion forms two limiting flanges, and after the left and right sides of the metal mesh 2 are fixed at the mounting position corresponding to the air inlet casing 6, the two limiting flanges can effectively limit the left and right sides of the air inlet cover, so as to prevent the air inlet cover from moving due to left and right movement, and ensure that the relative left and right position relationship between the air inlet cover and the air inlet casing 6 meets the design requirements.
In a preferred embodiment of the present invention, the height of the side of the U-shaped open slot close to the central axis is 1mm greater than the height of the side of the U-shaped open slot far from the central axis.
In this embodiment, two the height of spacing flange on the installation limit 3 is 1mm, because in the use, the horizontal force that spacing flange received is less, consequently, the height that spacing flange can set up is less to simplify processing, practice thrift the cost.
As shown in fig. 4 to 6, in a preferred embodiment of the present invention, the mounting bracket 4 includes:
the mounting frame main body 41 is fixedly arranged at two ends of the metal net 2 perpendicular to the central axis, and the shape of the mounting frame main body is matched with the shape of the cross section profile of the metal net 2;
and the bolt connecting pieces 42 are symmetrically fixed on the mounting frame main body 41 and are provided with through holes for fixing two ends of the metal net 2 at the corresponding mounting positions of the air inlet casing 6 through bolts.
In this embodiment, the mounting bracket main part 41 is fixed to be set up the both ends of the perpendicular axis of metal mesh 2, and the shape and the cross section profile shape phase-match of metal mesh 2 both play the connection effect, can also maintain the metal mesh 2 shape simultaneously, prevent that metal mesh 2 from taking place to warp. The bolt connecting sheet 42 facilitates the two ends of the metal net 2 to be firmly fixed at the corresponding mounting positions of the air inlet casing 6 through bolts, and the mounting and dismounting are convenient and reliable.
In a preferred embodiment of the invention, the surface of the metal mesh 2 is provided with a hydrophobic coating having a contact angle of more than 120 °.
In this embodiment, the surface of the metal mesh 2 is further provided with a hydrophobic coating, and the hydrophobic coating meets the requirement of the GJB 2525 on anti-icing performance, so that the air inlet hood can be further prevented from being blocked by the icing adhesion of water vapor, the air inlet airflow can still enter the engine from the side surface under the icing condition, the engine air inlet channel can not be blocked by a large area, and the defect that the air inlet channel is easily blocked by the single-plane air inlet hood under the icing condition can be effectively overcome.
In the preferred embodiment of the invention, the aero-engine intake cover further comprises a reinforcing rib 1 attached to the outer side of the metal net 2, and two ends of the reinforcing rib 1 are fixedly connected with the mounting edges 3 connected with the left side and the right side of the metal net 2 respectively.
Because the thickness of metal mesh 2 is generally less, in order to prevent metal mesh 2 from deforming under the action of external force, this embodiment prevents metal mesh 2 from deforming by setting up strengthening rib 1 to play the structure reinforcing effect to metal mesh 2.
As shown in fig. 4 and 8, in a preferred embodiment of the present invention, a relief plane 7 is centrally disposed in the middle of the cross section of the metal mesh 2, the middle of the reinforcing rib 1, and the middle of the mounting bracket 4, wherein the width of the relief plane 7 does not exceed one fifth of the arc length of the cross section of the metal mesh 2, the arc length of the reinforcing rib 1, and the arc length of the mounting bracket 4.
The setting of stepping down plane 7 in this embodiment can prevent effectively that the inlet hood from taking place to interfere with other positions of engine in the installation and causing the damage, moreover, because the width of stepping down plane 7 is no longer than 2 cross section arc lengths of metal mesh, 1 arc length of strengthening rib, 4 arc lengths of mounting bracket one fifth, consequently, even when stepping down plane 7 just freezes the back to the air current direction, the air current of admitting air still can get into the engine from the side of other curved sections of metal mesh 2, assurance that can be better is under the condition of freezing, be unlikely to the large tracts of land and block up the engine intake duct.
As shown in fig. 9, in the installation process, the left half intake cover and the right half intake cover which are symmetrically arranged are installed at the air inlet of the intake casing 6, when in installation, the U-shaped open slots of the installation edges 3 of the left half intake cover and the right half intake cover are matched with the arc-shaped flanges of the installation positions corresponding to the intake casing 6, then bolts are inserted into the installation frame 4, and the left half intake cover and the right half intake cover are connected to form a complete annular aero-engine intake cover which is fixed at the installation positions corresponding to the intake casing 6, so that the installation of the intake cover 5 can be completed. When the air inlet cover is disassembled, the air inlet cover 5 can be disassembled from the air inlet casing 6 only by taking down the bolt, and the whole assembling and disassembling process is rapid and convenient.
The air inlet cover can effectively prevent foreign objects (such as sand, tree branches, birds and the like) from entering the engine, protect the rotating parts of the engine and prolong the reliable service life of the engine; the air inlet cover is simple in structure, the two semi-annular left half air inlet covers and the right half air inlet covers are composed of the mounting edge 3, the mounting frame 4, the metal net 2 and the reinforcing ribs 1, and the left half air inlet covers and the right half air inlet covers are connected through bolts. The intake hood structure design of the invention has extremely small obstruction to the intake airflow, the total intake pressure loss of the intake hood is about 1 percent smaller than that of the intake hood with a complex structure, and meanwhile, the intake hood structure design of the invention adopts the convex net cover with the cambered surface, so that the intake airflow can still enter the engine from the side surface of the metal net 2 under the icing condition, the intake passage of the engine can not be blocked in a large area, and the defect that the intake passage is easy to be blocked by the single-plane intake hood under the icing condition is effectively solved.
The air inlet cover is verified in the air blowing and whole machine test of the component air inlet passage, and the total pressure loss can be effectively reduced; the air inlet cover is tested with the aviation turboprop engine in over 100 hours, and the operation is good.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement 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 inlet hood, its characterized in that, half left inlet hood and half right inlet hood that set up including the symmetry, half left inlet hood and half right inlet hood all include:
the plane development of the metal net (2) is rectangular, the central axis is bent into an arc shape, and the cross section profiles of the metal net (2) perpendicular to the central axis are bent into arc shapes and are consistent in size;
the mounting edges (3) are symmetrically arranged at the arc-shaped edges of the left side edge and the right side edge of the metal net (2) and are parallel to the central axis, and are used for fixing the left side edge and the right side edge of the metal net (2) at the corresponding mounting positions of the air inlet casing (6);
and the mounting frame (4) is fixedly arranged at two ends of the vertical central axis of the metal net (2), the shape of the metal net is matched with the cross section outline shape of the metal net (2), and the left half air inlet cover and the right half air inlet cover are connected to form a complete annular aero-engine air inlet cover.
2. The aircraft engine inlet cowl according to claim 1,
the central axis of the metal net (2) is bent into a semicircle.
3. The aircraft engine inlet cowl according to claim 1 or 2,
the metal net (2) is bent into a semicircle with the contour of each cross section vertical to the central axis of the metal net and has the same size.
4. The aircraft engine inlet cowl according to claim 1,
the U-shaped open slot is formed in the inner concave side of the mounting edge (3) along the length direction, and the U-shaped open slot is matched with the arc-shaped flange of the mounting position corresponding to the air inlet casing (6).
5. The aircraft engine inlet cowl according to claim 4,
the height of one side, close to the central axis, of the U-shaped open slot is greater than the height of one side, far away from the central axis, of the U-shaped open slot.
6. The aircraft engine inlet cowl according to claim 5,
the height ratio that U type open slot is close to axis one side the U type open slot is kept away from 1 ~ 2mm highly big of axis one side.
7. The aircraft engine inlet cowl according to claim 1,
the mounting frame (4) comprises:
the mounting rack main body (41) is fixedly arranged at two ends of the metal net (2) perpendicular to the central axis and is matched with the cross section outline shape of the metal net (2);
and the bolt connecting pieces (42) are symmetrically fixed on the mounting frame main body (41) and are provided with through holes for fixing the two ends of the metal net (2) at the corresponding mounting positions of the air inlet casing (6) through bolts.
8. The aircraft engine inlet cowl according to claim 1,
the surface of the metal net (2) is provided with a hydrophobic coating, and the contact angle of the hydrophobic coating is larger than 120 degrees.
9. The aircraft engine inlet cowl according to claim 1,
still include strengthening rib (1), attached setting is in the metal mesh (2) outside, the both ends of strengthening rib (1) respectively with install limit (3) fixed connection of the left and right sides of being connected metal mesh (2).
10. The aircraft engine inlet cowl according to claim 9,
the middle part of the cross section of the metal net (2), the middle part of the reinforcing rib (1) and the middle part of the mounting rack (4) are provided with a yielding plane (7) in the middle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011179125.7A CN112324573B (en) | 2020-10-29 | 2020-10-29 | Aeroengine air inlet cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011179125.7A CN112324573B (en) | 2020-10-29 | 2020-10-29 | Aeroengine air inlet cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112324573A true CN112324573A (en) | 2021-02-05 |
| CN112324573B CN112324573B (en) | 2022-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011179125.7A Active CN112324573B (en) | 2020-10-29 | 2020-10-29 | Aeroengine air inlet cover |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB671427A (en) * | 1949-08-30 | 1952-05-07 | Rolls Royce | Improvements in or relating to gas-turbine engines |
| EP2282031A1 (en) * | 2009-07-02 | 2011-02-09 | Eurocopter Deutschland GmbH | Filtering device with integrated bypass for an air inlet |
| CN205806018U (en) * | 2016-06-22 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of cartridge receiver connection structure |
| CN108361110A (en) * | 2017-01-27 | 2018-08-03 | 通用电气波兰有限责任公司 | Entrance mesh screen for aircraft engine |
| CN108688824A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Engine intake deicing system, internal combustion engine and aircraft |
| CN110497162A (en) * | 2019-09-23 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of processing method of aero-engine casing |
-
2020
- 2020-10-29 CN CN202011179125.7A patent/CN112324573B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB671427A (en) * | 1949-08-30 | 1952-05-07 | Rolls Royce | Improvements in or relating to gas-turbine engines |
| EP2282031A1 (en) * | 2009-07-02 | 2011-02-09 | Eurocopter Deutschland GmbH | Filtering device with integrated bypass for an air inlet |
| CN205806018U (en) * | 2016-06-22 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of cartridge receiver connection structure |
| CN108361110A (en) * | 2017-01-27 | 2018-08-03 | 通用电气波兰有限责任公司 | Entrance mesh screen for aircraft engine |
| CN108688824A (en) * | 2017-04-10 | 2018-10-23 | 清华大学 | Engine intake deicing system, internal combustion engine and aircraft |
| CN110497162A (en) * | 2019-09-23 | 2019-11-26 | 无锡航亚科技股份有限公司 | A kind of processing method of aero-engine casing |
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| Publication number | Publication date |
|---|---|
| CN112324573B (en) | 2022-03-25 |
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