Aero-engine compressor blade cleaning spray rod with resistance reduction effect

Abstract

The invention discloses an aero-engine compressor blade cleaning spray rod with a resistance reduction effect. The aero-engine compressor blade cleaning spray rod comprises a cleaning spray rod body for changing cleaning liquid into small liquid drops and even atomizing the small liquid drops. The water inlets belong to eccentric holes, are respectively formed in the two half parts of the swirler and are symmetrical along the axis, the cleaning liquid is in a high-speed rotating state after entering the swirler, so that centrifugal force is generated, and when the flow and pressure of the external cleaning liquid are relatively large, the swirler can change the cleaning liquid into small liquid drops and even atomize the small liquid drops; the cleaning fluid is sprayed out of the nozzle hole of the connecting rod to fully wash the blade, so that the cleaning fluid can be uniformly sprayed to the blade part of the gas compressor, the blade is effectively washed and cleaned, and the problem that the water body can fully wash spare parts only after the engine is decomposed into the spare parts in ultrasonic cleaning is solved.

Description

Technical Field

[0001] The invention relates to an aero-engine compressor blade cleaning spray rod with drag reduction effect, belonging to the technical field of aero-engines. Background Art

[0002] As the power source of aircraft, the performance of aircraft engines directly affects the safety and efficiency of aircraft. In aircraft engines, compressor blades play a key role, responsible for compressing air and sending it into the combustion chamber, which is the basis for the operation of the entire engine. However, long-term operation will cause various dirt to accumulate on the surface of the blades, such as dust, grease, crystals, etc. These dirt will reduce the aerodynamic performance of the blades and even affect the working efficiency of the entire engine. In order to maintain the efficient operation of the engine, the compressor blades need to be cleaned regularly.

[0003] At present, the blades are cleaned by ultrasonic machine (see Chinese patent publication number CN110053785A). Although the blades can be cleaned by ultrasonic, the ultrasonic cleaning requires the engine to be decomposed into parts before the water can fully wash the parts. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides an aircraft engine compressor blade cleaning spray rod with drag reduction effect.

[0005] The present invention is achieved through the following technical solutions.

[0006] The present invention provides an aircraft engine compressor blade cleaning spray rod with drag reduction effect, comprising:

[0007] A cleaning spray bar that turns cleaning fluid into small droplets or even atomization.

[0008] The cleaning spray rod comprises a connecting rod for conveying cleaning liquid and a cyclone for converting the cleaning liquid into small droplets or even atomizing the liquid in the connecting rod and then spraying the liquid out.

[0009] A pipe joint is installed at the end of the connecting rod.

[0010] The connecting rod end on which the pipe joint is installed is fixedly connected with a flange.

[0011] A channel hole is provided inside the center of the connecting rod axis, and the cleaning liquid flows through the channel hole when the connecting rod is transported. The channel hole runs through both ends of the connecting rod, and the channel hole is connected to the pipe joint.

[0012] The upper and lower surfaces of the connecting rod away from the pipe joint are cut into two planes, the upper plane is provided with a cylindrical pit, a cyclone is welded in the cylindrical pit, and the lower plane is provided with a nozzle hole.

[0013] The connecting rod far away from the pipe joint is provided with a plug to seal and block the end of the channel hole.

[0014] The cyclone is in a step shape, the large end of the cyclone is located outside the cylindrical pit for welding and fixing, and the small end of the cyclone is located inside the cylindrical pit.

[0015] A spray hole is arranged in the vertical center of the cyclone, and the spray hole is coaxial with the nozzle hole.

[0016] The cyclone is provided with a water inlet which is an eccentric hole, and there are two water inlets symmetrically distributed on the cyclone; the water inlet is connected to the nozzle hole through the spray hole.

[0017] The beneficial effects of the present invention are as follows: the water inlet is an eccentric hole, the water inlet is respectively located in the two halves of the cyclone and is symmetrical along the axis, the cleaning liquid is in a high-speed rotating state after entering the cyclone, thereby generating centrifugal force, when the external cleaning liquid flow and pressure are large, the cyclone can turn the cleaning liquid into small droplets or even atomized, and spray it out from the nozzle hole of the connecting rod to fully wash the blades, so that the cleaning liquid can be evenly sprayed to the compressor blade part, so that the blades are effectively washed and cleaned, solving the problem that ultrasonic cleaning requires the engine to be decomposed into parts before the water body can fully wash the parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the structure of the present invention when it is installed;

[0019] Figure 2 It is a schematic diagram of the structure of the present invention when it is installed;

[0020] Figure 3 It is a cross-sectional schematic diagram of the present invention when installed;

[0021] In the figure: 1-connecting rod; 11-nozzle hole; 12-pipe joint; 13-flange; 14-channel hole; 2-cyclone; 21-spray hole; 22-water inlet; 3-plug. DETAILED DESCRIPTION

[0022] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0023] like Figures 1 to 3 shown.

[0024] The present application discloses an aircraft engine compressor blade cleaning spray bar with drag reduction effect, comprising:

[0025] A connecting rod 1 with a pipe joint 12 is installed at the end thereof, and the connecting rod 1 is butted against a pipe for conveying water through the pipe joint 12 .

[0026] The end of the connecting rod 1 equipped with the pipe joint 12 is fixedly connected with a flange 13, and the connecting rod 1 can be fixed to the aircraft engine through the flange 13 to bear the force.

[0027] A channel hole 14 is provided inside the center of the axis of the connecting rod 1 , and the cleaning liquid flows through the channel hole 14 when the connecting rod 1 is transported. The channel hole 14 runs through both ends of the connecting rod 1 , and the channel hole 14 is connected to the pipe joint 12 .

[0028] The upper and lower surfaces of the connecting rod 1 away from the pipe joint 12 are cut into two planes. The upper plane is provided with a cylindrical pit in which a cyclone 2 is welded, and the lower plane is provided with a nozzle hole 11.

[0029] The connecting rod 1 away from the pipe joint 12 is installed with a plug 3 through interference fit or a threaded pair to seal and block the end of the channel hole 14.

[0030] The cyclone 2 is stepped, with the large end of the cyclone 2 outside the cylindrical pit and the small end of the cyclone 2 inside the cylindrical pit. A spray hole 21 is provided in the vertical center of the cyclone 2, and the spray hole 21 is coaxial with the nozzle hole 11.

[0031] The cyclone 2 is provided with a water inlet 22 which is an eccentric hole, and there are two water inlets 22 symmetrically distributed on the cyclone 2. The water inlet 22 is connected to the nozzle hole 11 through the spray hole 21.

[0032] The cleaning liquid enters the cyclone 2 from the channel hole 14, and enters the cyclone 2 through two water inlets 22. The water inlets 22 of the cyclone 2 are eccentric holes. The water inlets 22 are respectively located in two halves of the cyclone 2 and are symmetrical along the axis. After the cleaning liquid enters the cyclone 2, it will be in a high-speed rotation state, thereby generating centrifugal force. When the flow rate and pressure of the external cleaning liquid are large, the cyclone 2 can turn the cleaning liquid into small droplets or even atomize, and spray it from the nozzle hole 11 of the connecting rod 1 to fully wash the blades, so that the cleaning liquid can be evenly sprayed to the compressor blades, so that the blades are effectively washed and cleaned, which solves the problem that ultrasonic cleaning requires the engine to be decomposed into parts before the water body can fully wash the parts.

Claims

1. An aircraft engine compressor blade cleaning spray bar with drag reduction effect, characterized in that: include: A cleaning spray bar that turns cleaning fluid into small droplets or even atomization.

2. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 1, characterized in that: The cleaning spray rod comprises a connecting rod (1) for conveying cleaning liquid and a cyclone (2) for converting the cleaning liquid into small droplets or even atomizing the liquid in the connecting rod (1) and then spraying the liquid out.

3. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 2, characterized in that: A pipe joint (12) is installed at the end of the connecting rod (1); The end of the connecting rod (1) on which the pipe joint (12) is installed is fixedly connected to a flange (13).

4. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 2, characterized in that: A channel hole (14) is provided inside the center of the axis of the connecting rod (1), and the cleaning liquid flows through the channel hole (14) when the connecting rod (1) is transported. The channel hole (14) runs through both ends of the connecting rod (1), and the channel hole (14) is connected to the pipe joint (12).

5. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 4, characterized in that: The upper and lower surfaces of the connecting rod (1) away from the pipe joint (12) are cut into two planes, the upper plane is provided with a cylindrical pit, a cyclone (2) is welded in the cylindrical pit, and the lower plane is provided with a nozzle hole (11).

6. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 4, characterized in that: The connecting rod (1) away from the pipe joint (12) is provided with a plug (3) to seal and block the end of the channel hole (14).

7. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 2, characterized in that: The cyclone (2) is in a step shape, the large end of the cyclone (2) is located outside the cylindrical pit for welding and fixing, and the small end of the cyclone (2) is located inside the cylindrical pit.

8. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 7, characterized in that: A spray hole (21) is provided in the vertical center of the cyclone (2), and the spray hole (21) is coaxial with the nozzle hole (11).

9. The aircraft engine compressor blade cleaning spray bar with drag reduction effect as claimed in claim 1, characterized in that: The cyclone (2) is provided with a water inlet (22) which is an eccentric hole. The water inlets (22) are two symmetrically distributed on the cyclone (2). The water inlets (22) are connected to the nozzle hole (11) through the spray hole (21).

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