Frost prevention device of aerospace engine

Abstract

The utility model discloses a frost prevention device of an aerospace engine, and relates to the technical field of aerospace engine frost prevention, the frost prevention device of the aerospace engine comprises a mounting ring, the inner wall of the mounting ring is fixedly connected with a first mounting plate, and the lower side surface of the first mounting plate is fixedly connected with a condenser pipe; the upper side surface of the first mounting plate is fixedly connected with a compressor, the compressor is connected with a condensation pipe, the inner wall of the mounting ring is fixedly connected with two first guide rods, and the outer surfaces of the two first guide rods are slidably sleeved with displacement seats. The corners of the cleaning brush are cleaned, the problem that frost layers at the corners are difficult to clean and thickened is solved, meanwhile, the transverse moving assembly automatically moves transversely in the moving process of the cleaning brush, the cleaning range of the cleaning brush is increased, and cleaning dead corners are further reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to aerospace engine frost prevention technical field, in particular to a kind of frost prevention device of aerospace engine. BACKGROUND

[0002] Power is the key to high-speed flight, so the requirements for the engine are also very high. After the airflow passes through the inlet, the static temperature rises, which not only limits the further improvement of the compressor pressure ratio, but also reduces the heating ratio of the combustion chamber, thereby reducing the combustion efficiency and the thrust coefficient, making it difficult to improve and maintain the speed. Therefore, the pre-cooling technology for cooling the air entering the engine has been increasingly valued. A pre-cooler is installed between the inlet and the compressor to cool the high-temperature gas of the inlet airflow, reducing the air temperature, which can significantly improve the compressor pressure ratio and thus improve the engine thrust.

[0003] As the Chinese utility model patent with the patent publication number CN220285867U, including first device shell, first chute and second device shell, the inner wall of the first device shell is provided with a first chute, and the inside of the first chute is provided with a first sliding block, the outer side of the first sliding block is connected with the second device shell, and the outer side of the second device shell is uniformly provided with an extrusion block, the bottom of the inside of the first device shell is provided with a protective shell, and the top of the inside of the protective shell is provided with a first motor, the bottom of the inner wall of the second device shell is provided with a first toothed plate, the patent drives the second device shell to rotate by the first motor through the first gear, and at the same time drives the cavity to move the top rod, when the top rod is moved, the top block is moved, so that the device can be installed at different positions during use.

[0004] However, when using the defrosting plate to defrost the condensing pipe, only the vertical part of the condensing pipe can be defrosted, and the defrosting effect at the corner is not ideal, which can easily cause the frost layer at the corner to thicken, thereby affecting the normal operation of the device, and there are certain deficiencies. In view of this, we propose a frost prevention device for aerospace engine. UTILITY MODEL CONTENTS

[0005] The utility model aims to provide a frost prevention device for aerospace engine to solve the problems raised in the background technology.

[0006] In order to achieve the above object, the utility model provides the following technical scheme: A frost prevention device of aerospace engine, including the mounting ring, the inner wall of mounting ring is fixedly connected with first mounting plate, the downside surface of first mounting plate is fixedly connected with condenser pipe, the upside surface of first mounting plate is fixedly connected with compressor, the compressor is connected with condenser pipe, the inner wall of mounting ring is fixedly connected with two first guide rods, the outer surface of two first guide rods all is slidingly provided with displacement seat, the front and rear two side surfaces of two displacement seats all are fixedly connected with first mounting lug, left and right two first mounting lug are fixedly connected with first limit rod, the outer surface of first limit rod is slidingly provided with displacement plate, the side surface of displacement plate close to condenser pipe is fixedly connected with cleaning brush, the side surface of opposite of front and rear two cleaning brush all is fixedly connected with two second mounting lug, two second mounting lug between fixedly connected with second limit rod, be provided with horizontal moving assembly on mounting ring.

[0007] Preferably, the horizontal moving assembly includes a second mounting plate, the lower end of the second mounting plate is fixedly connected with the inner wall of the mounting ring, the upper end of the second mounting plate is fixedly connected with the first mounting plate, and the side surface of the second mounting plate close to the displacement plate is fixedly connected with a trapezoidal protrusion.

[0008] Preferably, the trapezoidal protrusion is in contact with the second mounting lug, and the inner wall of the mounting ring is fixedly connected with a collection box.

[0009] Preferably, the upper side surface of the collection box is provided as an inclined surface, and the upper side surface of the collection box is provided with a through groove extending into the interior thereof.

[0010] Preferably, the lower side surface of the collection box is provided with a discharge pipe, and the end of the discharge pipe away from the collection box extends out of the exterior of the mounting ring.

[0011] Preferably, the front side surface of the collection box is fixedly connected with a motor, and the output end of the motor is fixedly connected with a threaded rod.

[0012] Preferably, the outer surface of the threaded rod is threadedly provided with a displacement sleeve, the displacement sleeve is slidingly provided on the outer surface of the second limit rod, and the rear side surface of the collection box is fixedly connected with a second guide rod.

[0013] Preferably, the outer surface of the second guide rod is also slidingly connected with a displacement sleeve, and the displacement sleeve on the second guide rod is slidingly connected with the rear side second limit rod.

[0014] Compared with the prior art, the utility model has the beneficial effects that:

[0015] 1. The frost prevention device of the aerospace engine, through the flexible setting of the cleaning brush, can clean the corner part of the condenser pipe while reducing the damage to the condenser pipe, avoid the problem that the frost layer is difficult to clean and thickened at the corner part, and the horizontal moving assembly moves spontaneously during the movement of the cleaning brush, increases the cleaning range of the cleaning brush, and further reduces the cleaning dead angle.

[0016] 2. The frost prevention device of the aerospace engine, through the setting of the collecting box, the frost can be collected by the collecting box after being scraped off, and then discharged through the discharge pipe after being made into water, so that the scraped frost is prevented from accumulating in the interior of the mounting ring. BRIEF DESCRIPTION OF DRAWINGS

[0017] The utility model will be further explained in connection with the drawings and embodiments:

[0018] Figure 1 It is the structure schematic diagram of the utility model of a kind of aerospace engine's frost prevention device;

[0019] Figure 2 It is the overall structure schematic diagram of the utility model;

[0020] Figure 3 It is the cleaning brush schematic diagram of the utility model;

[0021] Figure 4 It is Figure 2 Enlarged view of A in Figure.

[0022] Figures: 1, mounting ring;2, first mounting plate;3, condenser pipe;4, compressor;5, first guide rod;6, displacement seat;7, first mounting lug;8, first limit rod;9, displacement plate;10, cleaning brush;11, second mounting lug;12, second limit rod;13, second mounting plate;14, trapezoidal protrusion;15, collecting box;16, through slot;17, discharge pipe;18, motor;19, threaded rod;20, displacement sleeve;21, second guide rod. DETAILED DESCRIPTION

[0023] This part will describe the specific embodiments of the utility model in detail, the preferred embodiments of the utility model are shown in the drawings, the role of the drawings is to supplement the description of the text part with graphics, so that people can intuitively and visually understand each technical feature and overall technical scheme of the utility model, but it cannot be understood as the limitation of the protection scope of the utility model.

[0024] Please refer to Figures 1-4The utility model provides a technical scheme: A frost prevention device of aerospace engine, including installation ring 1, the inner wall fixed connection of installation ring 1 has first mounting plate 2, the downside surface fixed connection of first mounting plate 2 has condenser pipe 3, the upside surface fixed connection of first mounting plate 2 has compressor 4, compressor 4 is connected with condenser pipe 3, the inner wall fixed connection of installation ring 1 has two first guide rod 5, the outer surface of two first guide rod 5 is slidably sleeved with displacement seat 6, the front and rear two side surfaces of two displacement seat 6 are all fixedly connected with first mounting lug 7, and the left and right two first mounting lug 7 are directly fixedly connected with first limit rod 8, and the outer surface of first limit rod 8 is slidably sleeved with displacement plate 9, and the side surface close to condenser pipe 3 of displacement plate 9 is fixedly connected with cleaning brush 10, and the side surface opposite of front and rear two cleaning brush 10 is all fixedly connected with two second mounting lug 11, and two second mounting lug 11 are fixedly connected with second limit rod 12, and installation ring 1 is provided with horizontal displacement assembly, through the flexible setting of cleaning brush 10, can reduce the harm to condenser pipe 3 at the same time, to the corner place of it is cleaned, avoid the problem that corner place is difficult to clean frost layer thickening, simultaneously with the aid of horizontal displacement assembly in the process of cleaning brush 10 movement spontaneously carries out horizontal displacement, increases the cleaning range of cleaning brush 10, and further reduces the cleaning dead angle.

[0025] Further, the horizontal displacement assembly includes a second mounting plate 13, the lower end of the second mounting plate 13 is fixedly connected with the inner wall of the installation ring 1, the upper end of the second mounting plate 13 is fixedly connected with the first mounting plate 2, the side surface close to the displacement plate 9 of the second mounting plate 13 is fixedly connected with a trapezoidal protrusion 14, the trapezoidal protrusion 14 is in contact with the second mounting lug 11, the inner wall of the installation ring 1 is fixedly connected with a collection box 15, the upper side surface of the collection box 15 is provided as an inclined surface, the upper side surface of the collection box 15 is provided with a through slot 16 extending into the interior thereof, the lower side surface of the collection box 15 is provided with a discharge pipe 17, one end of the discharge pipe 17 away from the collection box 15 extends out of the exterior of the installation ring 1, the front side surface of the collection box 15 is fixedly connected with a motor 18, the output end of the motor 18 is fixedly connected with a threaded rod 19, the outer surface of the threaded rod 19 is threadedly sleeved with a displacement sleeve 20, the displacement sleeve 20 is slidably sleeved on the outer surface of the second limit rod 12, the rear side surface of the collection box 15 is fixedly connected with a second guide rod 21, the outer surface of the second guide rod 21 is also slidably connected with the displacement sleeve 20, the displacement sleeve 20 on the second guide rod 21 is slidably connected with the rear side second limit rod 12, through the setting of the collection box 15, the frost can be collected by the collection box 15 after being scraped off, and can be discharged through the discharge pipe 17 after being subsequently made into water, avoiding the accumulation of the scraped off frost inside the installation ring 1.

[0026] Wherein, the motor 18 is matched with the power supply, wire, controller, microcomputer and other structures, and the compressor 4 and the condenser pipe 3 are all existing structures, and the specific reference can be made to the patent publication number CN220285867U, and the detailed description is not made because it is not the main structure.

[0027] Working principle: when the frost layer on the condenser pipe 3 is removed, the motor 18 is started, the motor 18 drives the threaded rod 19 to rotate, and because the displacement sleeve 20 is indirectly limited in the movement track by the second limiting rod 12, the displacement seat 6 and the first guide rod 5, the threaded rod 19 will drive the displacement sleeve 20 to move in the vertical direction when the threaded rod 19 rotates, the displacement sleeve 20 moves synchronously with the second limiting rod 12 to drive the displacement plate 9 and the cleaning brush 10 to move, the cleaning brush 10 will be swept off the frost on the condenser pipe 3 when it moves, and the displacement seat 6 will move synchronously when the displacement plate 9 moves, and because the second mounting ear 11 is in contact with the trapezoidal protrusion 14, the second mounting ear 11 will be squeezed by the trapezoidal protrusion 14 when it descends, and horizontal translation will occur, the cleaning brush 10 will move when the second mounting ear 11 moves horizontally, and the cleaning brush 10 will move left and right to reduce the cleaning dead angle, and because the cleaning brush 10 can deform itself, the corners of the condenser pipe 3 can be cleaned, and the frost cleaned can fall on the upper side of the collection box 15, and through the slope on the collection box 15 and the through slot 16, the frost can enter the inside of the collection box 15, and after the frost in the collection box 15 changes into water, the water can be discharged to the outside through the discharge pipe 17.

[0028] The above embodiment of the utility model is described in detail in combination with the drawings, but the utility model is not limited to the above embodiment, and various changes can be made within the knowledge range of ordinary skilled persons in the technical field without departing from the purpose of the utility model.

Claims

1. Frost protection device for aerospace engines comprising a mounting ring (1), characterized in that: The inner wall of the mounting ring (1) is fixedly connected with a first mounting plate (2), the lower surface of the first mounting plate (2) is fixedly connected with a condenser pipe (3), the upper surface of the first mounting plate (2) is fixedly connected with a compressor (4), the compressor (4) is connected with the condenser pipe (3), the inner wall of the mounting ring (1) is fixedly connected with two first guide rods (5), the outer surfaces of the two first guide rods (5) are both slidably sleeved with displacement seats (6), the front and rear surfaces of the two displacement seats (6) are both fixedly connected with first mounting ears (7), the left and right first mounting ears (7) are directly fixedly connected with a first limiting rod (8), the outer surface of the first limiting rod (8) is slidably sleeved with a displacement plate (9), the side surface of the displacement plate (9) close to the condenser pipe (3) is fixedly connected with cleaning brushes (10), the side surfaces of the front and rear cleaning brushes (10) opposite to each other are both fixedly connected with two second mounting ears (11), the second limiting rod (12) is fixedly connected between the two second mounting ears (11), and the mounting ring (1) is provided with a transverse moving assembly.

2. An anti-icing device for an aerospace engine according to claim 1, wherein: The transverse moving assembly comprises a second mounting plate (13), the lower end of the second mounting plate (13) is fixedly connected with the inner wall of the mounting ring (1), the upper end of the second mounting plate (13) is fixedly connected with the first mounting plate (2), and the side surface of the second mounting plate (13) close to the displacement plate (9) is fixedly connected with a trapezoidal protrusion (14).

3. A frost protection device for an aerospace engine according to claim 2, wherein: The trapezoidal protrusion (14) is in contact with the second mounting ear (11), and the inner wall of the mounting ring (1) is fixedly connected with a collecting box (15).

4. A frost protection device for an aerospace engine according to claim 3, wherein: The upper surface of the collecting box (15) is provided as an inclined surface, and the upper surface of the collecting box (15) is provided with a through groove (16) extending into the interior thereof.

5. Frost protection for an aerospace engine according to claim 4, characterised in that: The lower surface of the collecting box (15) is provided with a discharge pipe (17), and the end, away from the collecting box (15), of the discharge pipe (17) extends out of the exterior of the mounting ring (1).

6. A frost protection device for an aerospace engine according to claim 5, characterised in that: The front surface of the collecting box (15) is fixedly connected with a motor (18), and the output end of the motor (18) is fixedly connected with a threaded rod (19).

7. A frost protection device for an aerospace engine according to claim 6, characterised in that: The outer surface of the threaded rod (19) is threadedly sleeved with a displacement sleeve (20), the displacement sleeve (20) is slidably sleeved on the outer surface of the second limiting rod (12), and the rear surface of the collecting box (15) is fixedly connected with a second guide rod (21).

8. A frost protection device for an aerospace engine according to claim 7, characterised in that: The outer surface of the second guide rod (21) is also slidably connected with the displacement sleeve (20), and the displacement sleeve (20) on the second guide rod (21) is slidably connected with the rear second limiting rod (12).

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