High-reliability long-life aero-engine air inlet passage co-sulfurization sealing structure

Abstract

The application discloses a high-reliability long-service-life air intake passage co-sulfurization sealing structure of an aero-engine, which comprises a bypass door flange and a rubber sealing ring, the bypass door flange comprises a first rubber plate and a second rubber plate, and the first rubber plate and the second rubber plate are connected through an air inlet channel and a rubber column; the rubber sealing ring comprises a first clamping portion and a second clamping portion, the second clamping portion comprises a second outer clamping portion, and a sawtooth portion is arranged on the second outer clamping portion. The connecting mode of the rubber sealing ring is changed to co-sulfurization with metal parts, so that the structure glue or fasteners and the like are reduced, the delicate process performance of the sealing rubber part and the bypass door is effectively improved, and the grade of the product is improved. The product appearance and delicate process performance are ensured, and the rubber sealing reliability is improved.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine components, and in particular relates to a highly reliable and long-life co-sulfurized sealing structure for the air intake of an aero-engine. Background Technology

[0002] There are approximately dozens of hydrodynamic seals on modern aero gas turbine engines. Various types of hydrodynamic seals are currently in use, typically including toothed seals, brush seals, and tight-gap seals.

[0003] Fluid dynamic seals in aero-engines generally refer to the dynamic seals where airflow leaves the main flow path and enters the secondary flow path. Examples include the seals at the inlet of a turbine engine to control gas leakage. These seals have a significant impact on the overall performance of aero-engines, but are easily overlooked in engineering applications. Therefore, improving seal design is crucial to enhancing overall engine performance. This paper discusses the benefits and potential of improving seal design.

[0004] Furthermore, the connection methods for rubber rings in engine sealing structures are mostly screwed, glued, and slotted connections. If a screwed connection is used, the edge of the flange needs to be widened, adding unnecessary weight and affecting the appearance; if a glued or slotted connection is used, the connection reliability will be reduced. Due to the influence of the sealing position, the sealing performance and reliability of the sealing structure are subject to high requirements. This requires structural adhesives or fasteners.

[0005] For example, CN102101104A, published on June 22, 2011, discloses a method for sealing and boosting thrust in aero-engines using sealant. This method involves applying sealant to the mating surfaces of each compressor casing and between the compressor casing and its mating surfaces. The sealant used is oil-resistant silicone. By applying sealant to the mating surfaces of each compressor casing, the sealing performance of the engine's internal flow channels is improved. However, this method uses adhesive bonding, which has low reliability and cannot meet the high safety requirements of aero-engines.

[0006] For example, CN102537350A, published on July 4, 2012, relates to a sealing ring. The sealing ring is annular in shape, and its cross-sectional shape is "W", having two outer walls on the outer side and two inner walls on the inner side. The sealing ring of this invention has poor support and is prone to collapse. Summary of the Invention

[0007] This invention provides a highly reliable and long-life co-vulcanized sealing structure for the air intake of an aero-engine. While ensuring the reliability of the rubber sealing structure, it also aims to achieve an aesthetically pleasing result by providing a new structure for connecting the rubber sealing ring to the metal component.

[0008] The technical solution of this invention is implemented as follows:

[0009] A highly reliable and long-life co-vulcanized sealing structure for the air intake of an aero-engine is characterized by comprising a bypass flange and a rubber sealing ring, wherein the bypass flange comprises a first rubber plate and a second rubber plate, and the first rubber plate and the second rubber plate are connected by an air intake channel and a rubber column.

[0010] The first rubber plate and the second rubber plate are respectively provided with a first lip and a second lip. The rubber sealing ring covers the first lip and the second lip. The rubber sealing ring includes a first locking portion and a second locking portion. The first locking portion and the second locking portion are respectively provided with a first groove and a second groove. The first lip and the second lip are respectively located in the first groove and the second groove.

[0011] The first locking part includes a first inner locking part and a first outer locking part, the first inner locking part and the first outer locking part form the first groove, and the first outer locking part is at the same height as the first lip.

[0012] The second locking part includes a second inner locking part and a second outer locking part, which form the second groove. The second lip is also provided with a support limiting end, the thickness of which is the same as the thickness of the second outer locking part. The second outer locking part is provided with a serrated part.

[0013] Furthermore, the bypass flange has an array of mounting holes, and the adhesive posts are provided between the mounting holes.

[0014] Furthermore, the adhesive column contains a metal component, which is bonded to the adhesive column using a vulcanization process.

[0015] The highly reliable, long-life co-vulcanized sealing structure for aero-engine inlets, as described in this invention, offers the following advantages: By changing the connection method of the rubber sealing ring to co-vulcanization with metal parts, the need for structural adhesives or fasteners is reduced, effectively improving the precision of the sealing rubber parts and bypass doors, and enhancing the product's quality. This ensures both the product's aesthetics and precision, while also improving the reliability of the rubber seal. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the closed state of the co-sulfurized sealing structure for the inlet of an aero-engine, which is of high reliability and long lifespan according to the present invention.

[0017] Figure 2 not yet Figure 1 Schematic diagram of the semi-open state of the medium-vulcanized sealing structure;

[0018] Figure 3 for Figure 1 Schematic diagram of the middle bypass door;

[0019] Figure 4 for Figure 3 The AA-direction sectional view mainly shows the installation diagram of the rubber sealing ring;

[0020] Figure 5 for Figure 4 A magnified view of a portion of the image. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.

[0022] like Figures 1 to 5 The high-reliability, long-life co-vulcanized sealing structure for the air intake of an aero-engine shown in this invention includes a bypass flange 10 and a rubber sealing ring. The bypass flange 10 includes a first rubber plate 101 and a second rubber plate 102, which are connected by an air intake passage 12 and a rubber column 13.

[0023] The first rubber plate 101 and the second rubber plate 102 are respectively provided with a first lip 103 and a second lip 104. A rubber sealing ring covers the first lip 103 and the second lip 104. The rubber sealing ring includes a first locking portion 111 and a second locking portion 112. The first locking portion 111 and the second locking portion 112 are respectively provided with a first groove and a second groove. The first lip 103 and the second lip 104 are respectively located in the first groove and the second groove.

[0024] The first locking part 111 includes a first inner locking part and a first outer locking part, the first inner locking part and the first outer locking part form a first groove, and the first outer locking part is at the same height as the first lip 103.

[0025] The second locking part 112 includes a second inner locking part 117 and a second outer locking part 118. The second inner locking part 117 and the second outer locking part 118 form a second groove. The second lip 104 is also provided with a support limiting end 105. The thickness of the support limiting end 105 is the same as the thickness of the second outer locking part 118. When the second locking part 112 is installed with the inner mounting edge of the fairing 14, its contact surface is flat, and the support limiting end 105 can isolate the second locking part 112 from contact with the high-temperature airflow inside the fairing 14, effectively protecting the second locking part 112 from the influence of the high-temperature airflow inside the fairing 14 and ensuring the stability of the second locking part 112.

[0026] The second outer locking part 118 is provided with a serrated part 119. When the bypass door is closed, the rubber sealing ring on the bypass door flange 10 achieves the seal between the bypass door flange 10 and the fairing 14. Since the contact surface between the bypass door flange 10 and the fairing 14 is curved, in order to ensure sufficient fit and improve the reliability of the seal, a serrated part 119 is provided on the contact surface with the fairing 14 to further improve the sealing performance.

[0027] Preferably, the bypass flange 10 has an array of mounting holes 106, and adhesive posts 13 are provided between the mounting holes 106.

[0028] Preferably, the rubber column 13 contains a metal component, which is bonded to the rubber column using a vulcanization process, providing good support strength and resistance to cracking. The vulcanized rubber column 13 can connect the first rubber plate 101 and the second rubber plate 102, exhibiting good structural stability and improving the reliability of the rubber seal.

[0029] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A highly reliable, long-life co-sulfurized sealing structure for the air intake of an aero-engine, characterized in that, It includes a bypass flange and a rubber sealing ring. The bypass flange includes a first rubber plate and a second rubber plate, which are connected by an air intake channel and a rubber column. The first rubber plate and the second rubber plate are respectively provided with a first lip and a second lip. The rubber sealing ring covers the first lip and the second lip. The rubber sealing ring includes a first locking portion and a second locking portion. The first locking portion and the second locking portion are respectively provided with a first groove and a second groove. The first lip and the second lip are respectively located in the first groove and the second groove. The first locking portion includes a first inner locking portion and a first outer locking portion, which form the first groove. The first outer locking portion is at the same height as the first lip. The second locking portion includes a second inner locking portion and a second outer locking portion, which form the second groove. The second lip is also provided with a supporting and limiting end, the thickness of which is the same as the thickness of the second outer locking portion. The second outer locking portion is provided with a serrated portion.

2. The high-reliability, long-life co-sulfurization sealing structure for aero-engine inlets according to claim 1, characterized in that, The bypass flange has an array of mounting holes, and the adhesive posts are provided between the mounting holes.

3. The high-reliability, long-life co-sulfurization sealing structure for aero-engine inlets according to claim 1, characterized in that, The adhesive column contains a metal component, which is bonded to the adhesive column using a vulcanization process.

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