Helicopter engine external air inlet device with heating and anti-icing functions
By designing an external heating component in the helicopter engine's air intake system and utilizing engine exhaust gas for heating, the problems of difficult disassembly and maintenance of existing anti-icing devices are solved, achieving lightweight and efficient anti-icing effects and ensuring engine safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-24
- Publication Date
- 2026-03-17
AI Technical Summary
Existing helicopter engine anti-icing devices are usually installed internally, resulting in poor anti-icing effect, difficulty in disassembly, poor maintenance implementation, and large structural weight.
Design a simple and easy-to-disassemble external air intake device for helicopter engines. The device uses a heating component between the air intake and exhaust ends, including an inner skin, a heating element, and an outer skin. Distributed heating is achieved through heating pipes and guide strips, and the engine exhaust gas is used as a heating source to prevent cold air from icing.
It achieves lightweight anti-icing function, simplifies the disassembly and assembly process, improves anti-icing effect, and ensures safe and stable engine operation.
Smart Images
Figure CN224002811U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of helicopter engine air intake devices, and particularly relates to an external air intake device for helicopter engines with heating and anti-icing functions. Background Technology
[0002] When helicopters fly at high altitudes, the outside air temperature can generally reach above -30°C. Low temperatures not only affect the turbine inlet temperature of the engine, but also cause damage to the engine blades due to water vapor icing. Therefore, it is necessary to install an air intake device with anti-icing function on the helicopter engine.
[0003] Anti-icing devices with relatively advanced technology are usually installed inside the helicopter engine power module. They have poor anti-icing effect, are difficult to disassemble, have poor maintenance implementation, and are usually quite heavy. Utility Model Content
[0004] Purpose of application: In view of the above-mentioned technical problems, the purpose of this application is to provide an external air intake device for helicopter engines that is simple in structure, easy to disassemble and assemble, lightweight, and has distributed heating and anti-icing functions.
[0005] This application provides an external air intake device for a helicopter engine with heating and anti-icing functions, the device comprising:
[0006] Intake end;
[0007] The exhaust end connects to the air intake lip of the helicopter engine;
[0008] A heating element is disposed between the air inlet and the air outlet, and the heating element is used to heat the air entering the helicopter engine.
[0009] Preferably, the heating element is saddle-shaped.
[0010] Preferably, the heating component includes:
[0011] Inner skin;
[0012] A heating assembly is disposed on the inner skin, the heating assembly being used to heat the air entering the helicopter engine;
[0013] The outer skin is disposed on the heating assembly.
[0014] Preferably, the heating assembly includes:
[0015] Heating pipes are evenly distributed on the inner skin;
[0016] A flow guide strip is disposed on the inner skin, and the flow guide strip rectifies the hot air.
[0017] Preferably, the heating pipe has an opening, and the hot gas flows out from the opening.
[0018] Preferably, the device further includes an inlet, disposed at one end of the heating pipe;
[0019] A drain nozzle is located at the other end of the heating pipe.
[0020] The beneficial technical effects of this application are as follows:
[0021] The application provides a simple, easy-to-assemble and disassemble, and lightweight external air intake device for helicopter engines, which can effectively meet the air intake requirements of helicopter engines when operating at low temperatures and has great promotion and application value. Attached Figure Description
[0022] Figure 1 This is an isometric view of an external air intake device for a helicopter engine with heating and anti-icing functions provided in an embodiment of this application;
[0023] Figure 2 This is a front view of an external air intake device for a helicopter engine with heating and anti-icing functions, provided in an embodiment of this application.
[0024] Wherein: 1-inner skin, 2-outer skin, 3-port skin, 4-guide strip, 5-first heating pipe, 6-second heating pipe, 7-internal threaded joint, 8-clamp, 9-cover plate, 10-air venting flange, 11-drain nozzle. Detailed Implementation
[0025] Please see Figure 1 , Figure 2 This application provides an external air intake device for a helicopter engine with distributed heating and anti-icing functions, including an inner skin, an outer skin, a port skin, a guide strip, a heating pipe, a threaded connector, a clamp, a cover plate, an air intake flange, and a drain nozzle.
[0026] The device is designed as a metal sheet metal sandwich structure. The inner skin 1 is welded from aluminum alloy sheet metal parts, the outer skin 2 is riveted from aluminum alloy sheet metal parts, and the port skin 3 is welded from aluminum alloy sheet metal parts. The first heating pipe 5 and the second heating pipe 6 are welded from stainless steel pipes and serve as carriers for hot air flow. The guide strip 4, with partial openings, is welded to the inner skin 1 to guide the dissipated hot air flow and to fix the heating pipes.
[0027] Furthermore, the heating pipeline, with an inlet flange 10, is used to introduce hot airflow.
[0028] Furthermore, the first heating pipe 5 and the second heating pipe 6 have evenly distributed openings in their walls to transfer hot airflow and evenly diffuse it to various parts of the air intake device, heating the cold air inside the inner skin 1 and preventing the cold air from sublimating and freezing on the inner surface of the inner skin 1, thus avoiding damage to the helicopter engine blades after being sucked in.
[0029] Furthermore, the first heating pipe 5 and the second heating pipe 6 are installed based on the inner skin contour, pass through the partial opening of the guide strip 4, and are connected by connecting and tightening with the internal threaded connector 7, ensuring the pipe is sealed.
[0030] Furthermore, clamps 8 are used to initially fix the first heating pipe 5 and the second heating pipe 6.
[0031] Furthermore, the outer skin 2 is fixed to the outside of the first heating pipe 5 and the second heating pipe 6, and the window is tightened by clamping and then riveted to the port skin 3 using rivets.
[0032] Furthermore, the port skin 3 is riveted to the port of the inner skin 1 using rivets.
[0033] Next, tighten clamp 8, seal cover plate 9, tighten clamp on window and rivet.
[0034] Furthermore, the first heating pipe 5 is equipped with a drain nozzle 11 to discharge the water that liquefies after the hot gas flow encounters the cold air.
[0035] Furthermore, the hot exhaust gas is discharged through the gap between the port skin 3 and the port of the inner skin 1.
[0036] In this application, the exhaust gas emitted during engine startup is used as heating gas and enters the heating pipeline to achieve the purpose of heating.
[0037] This application provides a helicopter engine external air intake device with a simple structure, convenient use, and distributed heating and anti-icing function. It fully considers the functional requirements and has good manufacturability and implementability. It can introduce and uniformly diffuse a large flow of hot air, heat the surface of the air intake, prevent cold air from icing and prevent water droplets adhering to the surface of the air intake from icing, and ensure the safe and stable operation of the helicopter engine.
[0038] In other embodiments of this application, see the appendix. Figure 1 , Figure 2 The present invention provides an external air intake device for a helicopter engine with heating and anti-icing functions, comprising: an inner skin 1, an outer skin 2, a port skin 3, a guide strip 4, a first heating pipe 5, a second heating pipe 6, an internal threaded connector 7, a clamp 8, a cover plate 9, an air intake flange 10, and a drain nozzle 11.
[0039] The inner skin 1 is manufactured using welding connections to ensure smooth surfaces on both the inner and outer skins, facilitating stable air intake for the helicopter engine. The outer skin 2 is manufactured using riveting connections, the port skin 3 is manufactured using riveting connections, and the heating pipes are manufactured using welding connections.
[0040] The guide strip 4 has a partial opening and is connected to the inner skin 1 by welding. It is used to guide the dissipated hot airflow and fix the first heating pipe 5 and the second heating pipe 6.
[0041] The first heating pipe 5 is equipped with an air inlet flange 10 for introducing hot airflow.
[0042] The first heating pipe 5 and the second heating pipe 6 have evenly spaced holes in their walls to transfer hot airflow and evenly diffuse it to all parts of the air intake device, heating the cold air inside the inner skin 1.
[0043] The first heating pipe 5 and the second heating pipe 6 are installed based on the inner skin contour, pass through the partial opening of the guide strip 4, and are connected by tightening the internal threaded connector 7.
[0044] Use clamp 8 to initially fix the first heating pipe 5 and the second heating pipe 6.
[0045] Use rivets to rivet the port skin 3 to the port of the inner skin 1.
[0046] Fix the outer skin 2 to the outside of the first heating pipe 5 and the second heating pipe 6, and tighten the window with clamps. Use rivets to rivet the outer skin 3 to the port.
[0047] Tighten clamp 8, seal cover plate 9, tighten clamps on window and rivet.
[0048] The drain nozzle 11 is welded to the second heating pipe 6 to drain the water that liquefies after the hot gas flow cools down.
[0049] Hot exhaust gas is discharged through the gap between the port skin 3 and the inner skin 1.
Claims
1. A helicopter engine external air intake device having a heating anti-icing function, characterized in that, The device comprises: an air intake end; an air outlet end connected to an air intake lip of a helicopter engine; a heating component arranged between the air intake end and the air outlet end, the heating component being configured to heat air entering the helicopter engine; wherein the heating component is saddle-shaped; the heating component comprises: an inner skin; a heating assembly arranged on the inner skin, the heating assembly being configured to heat air entering the helicopter engine; an outer skin arranged on the heating assembly; the heating assembly comprises: heating pipes distributed on the inner skin; a flow guide strip arranged on the inner skin, the flow guide strip being configured to straighten hot air; the heating pipes have openings through which the hot air flows out.
2. The apparatus of claim 1, wherein, The device further comprises: an entry nozzle arranged at one end of the heating pipes; a drainage nozzle arranged at the other end of the heating pipes.