An ice-prevention air-bleed structure on an air intake casing of an aero-engine

Abstract

The application belongs to the technical field of ice-preventing air-bleed structure design on an aero-engine air intake casing, and particularly relates to an ice-preventing air-bleed structure on an aero-engine air intake casing, which comprises a supporting ring sleeved on the outer periphery of the air intake casing, the inner front end of which is provided with an annular stop protrusion, and the rear end of which is provided with a plurality of supporting protrusions; the annular stop protrusion is abutted against the front end of the air intake casing; each supporting protrusion is connected to the head of a supporting plate through a screw, and is provided with an ice-preventing air hole which is communicated with an ice-preventing air inlet hole on the corresponding supporting plate head; the ice-preventing air-bleed structure on the aero-engine air intake casing further comprises a gas collecting cover which is annular, and the edges of the two ends of which are welded to the outer side of the supporting ring to form an annular gas collecting cavity between the supporting ring and the gas collecting cover, and the gas collecting cover is provided with an ice-preventing air-bleed hole; the annular gas collecting cavity is communicated with the ice-preventing air-bleed hole, and is also communicated with each ice-preventing air hole.

Description

Technical Field

[0001] This application belongs to the technical field of anti-icing bleed air structure design on the air intake casing of an aero-engine, specifically relating to an anti-icing bleed air structure on the air intake casing of an aero-engine. Background Technology

[0002] The air intake casing at the front end of the aero engine serves as the main load-bearing structure. Inside the casing, a support ring is installed. Multiple support plates are installed circumferentially between the air intake casing and the support ring for support. The heads of the support plates extend from the holes on the air intake casing for fixation.

[0003] To prevent icing of the support plates inside the air intake casing, each support plate is designed as a hollow structure with anti-icing air inlets on the plate heads and anti-icing exhaust ports on the plate walls. An annular gas collection shroud is also installed on the air intake casing, surrounding the outer perimeter of the air intake casing and forming an annular gas collection chamber with the air intake casing. This annular gas collection chamber communicates with each anti-icing air inlet. Anti-icing bleed-out ports are provided on the gas collection shroud. When the aero-engine is operating, anti-icing gas can be introduced into the annular gas collection chamber through these ports. The anti-icing gas then enters each support plate through the anti-icing air inlets and is subsequently discharged through the anti-icing exhaust ports on the plate walls, thus achieving the anti-icing effect for each support plate.

[0004] Currently, for ease of assembly, the air intake shroud is designed to be welded together from multiple arc-shaped blocks and directly connected to the intake casing. This technical solution has the following drawbacks:

[0005] 1) There are a large number of welds on the gas hood and intake casing. During the welding process, they are prone to significant deformation, which has an adverse effect on the load-bearing structure of the intake casing.

[0006] 2) The air intake shroud is welded to the intake casing as a whole. When the air intake shroud is damaged, the parts cannot be replaced separately, resulting in poor maintainability.

[0007] This application is made in view of the aforementioned technical deficiencies.

[0008] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0009] The purpose of this application is to provide an anti-icing bleed air structure on the air intake casing of an aircraft engine to overcome or mitigate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] An anti-icing bleed air structure for an aircraft engine inlet casing includes:

[0012] A support ring is fitted around the outer periphery of the intake casing. It has an annular stop protrusion inside the front end and multiple support protrusions at the rear end.

[0013] The annular stop protrusion abuts against the front end of the intake casing;

[0014] Each support boss is connected to the support plate head of a support plate by screws, and has an anti-icing vent hole that communicates with the anti-icing air inlet hole on the corresponding support plate head.

[0015] The anti-icing bleed air structure on the air intake casing of an aircraft engine also includes:

[0016] The gas collection hood is ring-shaped, with its two ends welded to the outside of the support ring, forming a ring-shaped gas collection cavity between it and the support ring. It has anti-icing air ducts on it.

[0017] The annular air collection chamber is connected to the anti-icing air intake hole and to each anti-icing vent hole.

[0018] According to at least one embodiment of this application, in the above-described anti-icing bleed air structure on the air intake casing of an aero-engine, the outer wall of the front end of the support ring has an annular reinforcing mounting edge.

[0019] According to at least one embodiment of this application, in the above-mentioned anti-icing air bleed structure on the air intake casing of the aero-engine, the outer wall of the support ring is recessed to form an annular groove, which constitutes an annular air collection chamber.

[0020] According to at least one embodiment of this application, in the above-mentioned anti-icing bleed air structure on the air intake casing of the aircraft engine, each support plate head has a connecting boss.

[0021] Each support protrusion is connected to its corresponding connecting boss by two screws.

[0022] According to at least one embodiment of this application, the above-described anti-icing bleed air structure on the aero-engine inlet casing further includes:

[0023] An air intake seat is welded into the anti-icing air intake hole, and it has an anti-icing air source connection hole.

[0024] The anti-icing gas source connection hole is connected to the annular gas collection chamber.

[0025] According to at least one embodiment of this application, the above-described anti-icing bleed air structure on the aero-engine inlet casing further includes:

[0026] Multiple sealing gaskets, each corresponding to a support boss and a support plate head. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the anti-icing bleed air structure on the air intake casing of an aircraft engine provided in an embodiment of this application;

[0028] Figure 2 This is a partial cross-sectional view of the anti-icing bleed air structure on the air intake casing of an aero-engine provided in an embodiment of this application;

[0029] in:

[0030] 1-Support ring; 2-Intake casing; 3-Support plate; 4-Gas collection hood; 5-Air intake seat; 6-Sealing gasket.

[0031] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0032] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0033] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0034] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0035] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0036] An anti-icing bleed air structure for an aircraft engine inlet casing includes:

[0037] Support ring 1 is fitted around the outer periphery of intake casing 2, with an annular stop protrusion inside the front end and multiple support protrusions at the rear end;

[0038] The annular stop protrusion abuts against the front end of the intake casing 2;

[0039] Each support boss is connected to the support plate head of a support plate 3 by screws, and has an anti-icing vent hole that communicates with the anti-icing air inlet hole on the corresponding support plate head.

[0040] The anti-icing bleed air structure on the air intake casing of an aircraft engine also includes:

[0041] The gas collection hood 4 is ring-shaped, with its two ends welded to the outside of the support ring 1, forming a ring-shaped gas collection cavity between it and the support ring. It has anti-icing air ducts.

[0042] The annular air collection chamber is connected to the anti-icing air intake hole and to each anti-icing vent hole.

[0043] The anti-icing bleed air structure on the air intake casing of the aircraft engine disclosed in the above embodiments can introduce anti-icing air into the annular air collection chamber through the anti-icing bleed air hole when the aircraft engine is working. The anti-icing air enters into each support plate 3 through each anti-icing vent hole and its anti-icing air inlet hole, and then is discharged through the anti-icing exhaust hole on the wall of each support plate 3, thereby achieving the anti-icing effect on each support plate 3.

[0044] In the anti-icing bleed air structure on the air intake casing of the aircraft engine disclosed in the above embodiments, the design involves welding the gas collection shroud 4 to the support ring 1. Multiple support bosses at the rear end of the support ring 1 are fastened to each support plate head with screws, thus fixing the gas collection shroud 4 in an assembled manner. This avoids the process defects of having many weld seams, and when the gas collection shroud 4 is damaged, the screws can be loosened, and the gas collection shroud 4 together with the support ring 1 can be removed from the air intake casing 2. After repair, it can be fastened back to the casing 2 with screws, which makes it easy to maintain and replace. In addition, the support ring 1 abuts against the front end of the air intake casing 2 through the annular stop protrusion inside the front end, and the stop is used for positioning, which can increase the overall stability of the structure.

[0045] In some optional embodiments, in the above-mentioned anti-icing air bleed structure on the air intake casing of the aero-engine, the outer wall of the front end of the support ring 1 has an annular reinforced mounting edge, which can enhance the stability of the structure and replace the original annular mounting edge at the front end of the air intake casing 2 for casing conversion. In addition, during the design, a certain gap can be maintained between the annular reinforced mounting edge and the air hood 4 so as to weld the air hood 4 to the support 1.

[0046] In some optional embodiments, in the above-mentioned anti-icing air bleed structure on the air intake casing of the aero-engine, the outer wall of the support ring 1 is recessed to form an annular groove, which constitutes an annular air collection chamber.

[0047] In some optional embodiments, in the above-described anti-icing bleed air structure on the air intake casing of the aero-engine, each support plate head has a connecting boss.

[0048] Each support protrusion is connected to its corresponding connecting boss by two screws.

[0049] In some optional embodiments, the above-described anti-icing bleed air structure on the aero-engine inlet casing further includes:

[0050] Air intake seat 5 is welded into the anti-icing air intake hole, and has an anti-icing air source connection hole on it;

[0051] The anti-icing gas source connection hole is connected to the annular gas collecting chamber. When the aero-engine is working, anti-icing gas can be introduced into the annular gas collecting chamber through the anti-icing gas source connection hole.

[0052] In some optional embodiments, the above-described anti-icing bleed air structure on the aero-engine inlet casing further includes:

[0053] Multiple sealing gaskets 6, each sealing gasket 6 is placed between a supporting boss and a connecting boss to enhance the sealing effect.

[0054] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0055] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An anti-icing bleed air structure for an aero-engine inlet casing, wherein a support ring is provided inside the inlet casing, and multiple support plates are arranged circumferentially between the inlet casing and the support ring, the support plates being hollow structures, characterized in that... include: The support ring (1) is fitted around the outer periphery of the intake casing (2), with an annular stop protrusion inside the front end and multiple support protrusions at the rear end; The annular stop protrusion abuts against the front end of the intake casing (2); Each support boss is connected to the support plate head of a support plate (3) by screws, and has an anti-icing vent hole that is connected to the anti-icing air inlet hole on the corresponding support plate head. The anti-icing bleed air structure on the aero-engine inlet casing also includes: The gas collection hood (4) is ring-shaped, with its two ends welded to the outside of the support ring (1), forming a ring-shaped gas collection cavity with the support ring. It has anti-icing air ducts. The annular air collection chamber is connected to the anti-icing air intake hole and to each anti-icing vent hole.

2. The anti-icing bleed air structure on the air intake casing of an aero-engine according to claim 1, characterized in that, The outer wall of the front end of the support ring (1) has an annular reinforcing mounting edge.

3. The anti-icing bleed air structure on the air intake casing of an aero-engine according to claim 1, characterized in that, The outer wall of the support ring (1) is concave, forming an annular groove, which constitutes an annular gas collection cavity.

4. The anti-icing bleed air structure on the air intake casing of an aero-engine according to claim 1, characterized in that, Each support plate head has a connecting boss; Each support protrusion is connected to its corresponding connecting boss by two screws.

5. The anti-icing bleed air structure on the air intake casing of an aero-engine according to claim 1, characterized in that, Also includes: The air intake seat (5) is welded into the anti-icing air intake hole and has an anti-icing air source connection hole; The anti-icing gas source connection hole is connected to the annular gas collection chamber.

6. The anti-icing bleed air structure on the air intake casing of an aero-engine according to claim 1, characterized in that, Also includes: Multiple sealing gaskets (6), each sealing gasket (6) is placed between a support boss and a support plate head.

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