Air intake volutes, aircraft engines, and aircraft equipment
By designing drainage and ventilation structures in the air intake casing and using high-temperature gas to melt frost, the problem of air intake casing icing in low-temperature environments has been solved, improving the safety and service life of aero engines.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- HUNAN GUOKE NEW ENERGY TECHNOLOGY CO LTD
- Filing Date
- 2025-09-18
- Publication Date
- 2026-07-07
AI Technical Summary
In low-temperature environments, aircraft engines are prone to icing on the intake volute, which narrows the passage and affects the operational safety of the aircraft engine.
An air intake volute structure is designed, including a first chamber and a second chamber, with a drain hole and a venting chamber. High-temperature gas generated by a heat source is introduced into the venting chamber through an air intake pipe, where heat energy melts the ice and water is discharged through the drain hole, thereby enhancing anti-icing and waterproof capabilities.
It effectively melts ice and frost inside the air intake casing, improving the operational safety and service life of aero engines and reducing water corrosion and oxidation.
Smart Images
Figure CN224469218U_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of engine technology, and more particularly to an air intake volute, an aero-engine, and aviation equipment. Background Technology
[0002] Aircraft engines provide the thrust required for aircraft to fly. When aircraft operate in low-temperature weather, high-altitude and frigid regions, or icy and snowy environments, cold airflow enters the air intake casing of the aircraft engine. This cold airflow is prone to icing in the air intake casing, causing the airflow passage in the air intake casing to narrow, affecting the air intake of the aircraft engine and reducing the safety of aircraft engine operation. Summary of the Invention
[0003] This application provides an air intake housing, an aircraft engine, and aviation equipment, aiming to improve the waterproof and anti-icing capabilities of the air intake housing.
[0004] An embodiment of the first aspect of this application provides an intake volute, comprising:
[0005] An air intake housing has an airflow channel, the airflow channel including a first chamber and a second chamber, the air intake housing including a drain hole communicating with the second chamber, and the first chamber communicating with the end of the second chamber opposite to the drain hole in a vertical direction;
[0006] A heating housing is disposed on the air intake housing. The heating housing and the air intake housing together form a ventilation cavity. The ventilation cavity is spaced apart from the first chamber. The heating housing has a first air inlet that communicates with the ventilation cavity.
[0007] An air intake pipe, the first end of which is connected to the first air inlet, and the second end of which is connected to a heat source.
[0008] In some embodiments, the intake housing further includes a first housing and a second housing connected to each other, the first housing having the first chamber and the second housing having the second chamber.
[0009] In some embodiments, the first air inlet is disposed on the side of the first housing opposite to the second housing;
[0010] The first housing also includes an exhaust port, which communicates with the ventilation cavity and is located on the side of the first housing near the second housing.
[0011] In some embodiments, the first housing and the second housing are both semi-annular, and the first housing and the second housing enclose a hollow cavity. At least a portion of the airflow channel is spaced apart from the hollow cavity and extends along the periphery of the hollow cavity. The ventilation cavity is an annular cavity that extends along a portion of the hollow cavity.
[0012] In some embodiments, the intake housing further includes a heating channel, at least a portion of which is disposed within the second chamber. One end of the heating channel is connected to the third end of the air intake pipe via a second air inlet disposed on the second housing, and the other end of the heating channel is connected to the outer ring assembly of the intake casing.
[0013] In some embodiments, the air intake housing includes a plurality of drain holes, which are spaced apart and communicate with the second chamber respectively.
[0014] In some embodiments, the air intake housing further includes a flushing inlet, which communicates with the first chamber.
[0015] In some embodiments, the intake volute further includes:
[0016] A temperature sensor is disposed on the air intake housing, and the temperature sensor is used to detect the temperature at the inlet of the airflow channel.
[0017] An embodiment of the second aspect of this application provides an aircraft engine, the aircraft engine including the air intake volute as described above.
[0018] An embodiment of the third aspect of this application provides an aircraft device including an air intake vortex as described above and / or an aircraft engine as described above.
[0019] In the air intake casing, aero-engine, and aviation equipment provided in this application embodiment, by setting the first chamber vertically connected to the end of the second chamber opposite to the drain hole, water can be discharged through the drain hole under gravity when it is present in the airflow channel, thereby improving the waterproof capability of the air intake casing, extending its service life, and reducing or preventing water corrosion and oxidation of the air intake casing. By setting a venting chamber spaced apart from the first chamber, the heating shell has a first air inlet connected to the venting chamber. The first end of the venting pipe is connected to the first air inlet, and the second end of the venting pipe is connected to a heat source, allowing high-temperature gas generated by the heat source to be guided into the venting chamber through the venting pipe. The heat energy of the high-temperature gas in the venting chamber is conducted to the air intake casing. In the event of ice formation in the first chamber, the heat energy of the high-temperature gas in the venting chamber can melt the ice. The melted water flows to the second chamber under gravity and is discharged through the drain hole connected to the second chamber, improving the anti-icing capability of the air intake casing. Attached Figure Description
[0020] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings, wherein the same or similar reference numerals denote the same or similar features.
[0021] Figure 1 This is a three-dimensional structural diagram of an intake volute provided in an embodiment of this application;
[0022] Figure 2 This is a schematic diagram of the planar structure of an intake volute provided in an embodiment of this application;
[0023] Figure 3 This application provides an embodiment of an intake volute along... Figure 2 A schematic diagram of the cross-sectional structure of line AA shown.
[0024] Figure 4 This is a schematic diagram of the planar structure of an intake volute provided in an embodiment of this application;
[0025] Figure 5 This is a schematic diagram of the airflow and water flow principle of an air intake volute provided in an embodiment of this application.
[0026] Explanation of reference numerals in the attached figures:
[0027] 10. Intake volute; heat source, 20;
[0028] 1. Inlet housing; 11. First housing; 12. Second housing; 13. Airflow channel; 13a. First chamber; 13b. Second chamber; 131. Drain hole; 14. Connecting seat; 15. Hollow cavity; 16. Second air inlet; 17. Heating channel; 18. Flushing inlet;
[0029] 2. Heating housing; 21. Vent chamber; 22. Exhaust port; 23. First air inlet;
[0030] 3. Airway tube; 31. First end; 32. Second end; 33. Third end;
[0031] 4. Temperature sensor;
[0032] X, vertical direction. Detailed Implementation
[0033] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.
[0034] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.
[0035] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. It should be noted that, unless otherwise specified, different features in the embodiments of this application can be combined with each other.
[0036] When using terms such as "above," "above," "below," "below," or "relative" to define the positional relationship between two elements, this includes not only the state where the two elements are directly connected, but also the state where the two elements are separated by gaps or other elements. Furthermore, the terms "first," "second," and "third," etc., are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.
[0037] Please see Figure 1 , Figure 2 Figure 3 This application provides an intake volute 10, which includes an intake housing 1, a heating housing 2, and an air intake pipe 3. The intake housing 1 has an airflow channel 13, which includes a first chamber 13a and a second chamber 13b. The intake housing 1 includes a drain hole 131 that communicates with the second chamber 13b. The first chamber 13a is connected to the end of the second chamber 13b away from the drain hole 131 along the vertical direction X. The heating housing 2 is disposed on the intake housing 1, and the heating housing 2 and the intake housing 1 together form a ventilation cavity 21. The ventilation cavity 21 is spaced apart from the first chamber 13a. The heating housing 2 has a first air inlet 23 that communicates with the ventilation cavity 21. The first end 31 of the air intake pipe 3 communicates with the first air inlet 23, and the second end 32 of the air intake pipe 3 is used to communicate with a heat source 20.
[0038] The air intake casing 10 provided in this application can be used in aircraft engines and aviation equipment. The air intake casing 1 encloses and forms an airflow channel 13, which has an inlet and an outlet. Optionally, the aircraft engine has an air intake system, which includes the air intake casing 10 and an air intake housing. The inlet of the airflow channel 13 of the air intake casing 10 is in communication with the external environment, and the outlet of the airflow channel 13 of the air intake casing 10 is in communication with the air intake of the engine through the air intake housing.
[0039] The connected first chamber 13a and second chamber 13b form all or part of the airflow channel 13. The inlet can be located in one of the first chamber 13a and the second chamber 13b, and the outlet can be located in one of the first chamber 13a and the second chamber 13b. For example, the inlet can be located in one of the first chamber 13a and the second chamber 13b, and the outlet can be located in the other of the first chamber 13a and the second chamber 13b. The airflow channel 13 of the intake volute 10 allows gas to flow into the aviation luminous device. The intake volute 10 can utilize the compressibility of air to absorb and smooth pressure fluctuations in the gas, providing a stable airflow.
[0040] The vertical direction X can be along the direction of gravity. The first chamber 13a is connected to the end of the second chamber 13b opposite to the drain hole 131 along the vertical direction X, that is, the first chamber 13a is located above the second chamber 13b. The heating shell 2 has a first air inlet 23 that connects to the venting chamber 21. The first end 31 of the air intake pipe 3 is connected to the first air inlet 23, and the second end 32 of the air intake pipe 3 is used to connect to the heat source 20, so that the high-temperature gas generated by the heat source 20 can be guided through the air intake pipe 3 to the first air inlet 23 and into the venting chamber 21, and the heat energy of the high-temperature gas in the venting chamber 21 is conducted to the intake shell 1. In the event of ice formation in the first chamber 13a, the heat energy of the high-temperature gas in the venting chamber 21 can melt the ice, and the melted water flows to the second chamber 13b under the action of gravity and is discharged from the drain hole 131 that connects to the second chamber 13b, thereby improving the anti-icing capability of the intake volute 10. Optionally, the heat source is the high-temperature gas at the compressor outlet.
[0041] In this application, by setting the first chamber 13a to be connected to the end of the second chamber 13b opposite to the drain hole 131 in the vertical direction X, water can be discharged through the drain hole 131 under gravity when water is present in the airflow channel 13, thereby improving the waterproof capability of the intake volute 10, increasing the service life of the intake volute 10, and reducing or avoiding water corrosion and oxidation of the intake volute 10; by setting the ventilation chamber 21 to be spaced apart from the first chamber 13a, the heating shell 2 has a first air inlet 23 connected to the ventilation chamber 21, the first end 31 of the air duct 3 is connected to the first air inlet 23, and the second end 32 of the air duct 3 is used to connect to the heat source 20, so that the high-temperature gas generated by the heat source 20 can be guided into the ventilation chamber 21 through the air duct 3, and the heat energy of the high-temperature gas in the ventilation chamber 21 is conducted to the intake shell 1. When ice forms in the first chamber 13a, the heat energy of the high-temperature gas in the ventilation chamber 21 can melt the ice. The melted water flows to the second chamber 13b under the action of gravity and is discharged from the drain hole 131 that connects to the second chamber 13b, thereby improving the anti-icing capability of the intake volute 10.
[0042] Please refer to the following: Figure 4In some embodiments, the intake housing 1 further includes a first housing 11 and a second housing 12 connected to each other, the first housing 11 having a first chamber 13a and the second housing 12 having a second chamber 13b.
[0043] The first housing 11 has openings at both ends that connect to the first chamber 13a, and the second housing 12 has openings at both ends that connect to the second chamber 13b. The first housing 11 and the second housing 12 are joined together such that the openings at both ends of the first housing 11 are connected to the openings at both ends of the second housing 12, and the two ends of the first chamber 13a are connected to the two ends of the second chamber 13b.
[0044] Both the first housing 11 and the second housing 12 can be castings, and both can be made of cast titanium alloy. Both the first housing 11 and the second housing 12 have protruding connecting seats 14. After the first housing 11 and the second housing 12 are assembled, the connecting seats 14 at one end of the first housing 11 and the connecting seats 14 at one end of the second housing 12 contact each other, and can be connected together using fasteners. The connecting seats 14 at the other end of the first housing 11 and the connecting seats 14 at the other end of the second housing 12 contact each other, and can be connected together using another fastener. Optionally, the fasteners are mating bolts and nuts. The connecting seats 14 of the first housing 11 and the connecting seats 14 of the second housing 12 are connected along the vertical direction X.
[0045] In some embodiments, the first air inlet 23 is disposed at one end of the first housing 11 away from the second housing 12; the first housing 11 also includes an exhaust port 22, which communicates with the ventilation chamber 21 and is disposed at one end of the first housing 11 near the second housing 12.
[0046] The high-temperature gas introduced from the air inlet pipe 3 can first enter the ventilation chamber 21 through the first air inlet 23, and then move along the ventilation chamber 21 to the exhaust port 22. This facilitates the movement of the high-temperature gas in the ventilation chamber 21 and helps to improve the temperature uniformity of various parts of the ventilation chamber 21.
[0047] In some embodiments, the first housing 11 and the second housing 12 are both semi-annular, and the first housing 11 and the second housing 12 enclose a hollow cavity 15. At least a portion of the airflow channel 13 is spaced from the hollow cavity 15 and extends along the periphery of the hollow cavity 15, so that the airflow channel 13 is an annular channel provided along the hollow cavity 15, which is beneficial for the intake housing 1 to stabilize the airflow in the airflow channel 13. The ventilation cavity 21 is an annular cavity that extends partially along the hollow cavity 15, so that the ventilation cavity 21 is adapted to the shape of the first chamber 13a, thereby increasing the contact area between the high-temperature gas in the ventilation cavity 21 and the first housing 11.
[0048] The ventilation chamber 21 can be a semi-annular cavity extending along a portion of the hollow cavity 15. Exhaust ports 22 are located at opposite ends of the ventilation chamber 21 near the second chamber 13b. High-temperature gas introduced from the air intake pipe 3 can first enter the ventilation chamber 21 through the first air inlet 23, and then be diverted along the ventilation chamber 21 to the two exhaust ports 22. This facilitates the movement of the high-temperature gas within the ventilation chamber 21 and improves the temperature uniformity throughout the ventilation chamber 21.
[0049] Please refer to the following: Figure 5 In some embodiments, the intake housing 1 further includes a heating channel 17, at least a portion of which is disposed within the second chamber 13b. One end of the heating channel 17 is connected to the third end of the air intake pipe 3 via a second air inlet 16 disposed on the second housing 12, and the other end of the heating channel 17 is used to connect to the outer ring assembly of the intake casing.
[0050] The air intake pipe 3 has at least one air inlet end, which is connected to the heat source 20. The air intake pipe 3 has at least two air outlet ends, which are connected to the first air inlet 23 and the second air inlet 16. Figure 5 The dashed line indicates the trajectory of airflow along the second air inlet 16 and the heating channel 17, as well as the trajectory of water flow along the second housing 12. At least a portion of the heating channel 17 is located within the second chamber 13b, allowing high-temperature gas introduced from the air intake pipe 3 to first enter the heating channel 17 through the second air inlet 16. The heat energy of the high-temperature gas in the heating channel 17 is conducted to the second chamber 13b, thereby increasing the temperature within the second chamber 13b and improving the anti-icing capability of the air intake volute 10.
[0051] In some embodiments, the air intake housing 1 includes a plurality of drain holes 131, which are spaced apart and communicate with the second chamber 13b respectively.
[0052] Setting multiple drainage holes 131 helps improve the drainage capacity of water flow within the airflow channel 13, preventing water from stagnating within the airflow channel 13.
[0053] In some embodiments, the intake housing 1 further includes a flushing inlet 18, which communicates with the first chamber 13a.
[0054] The flushing inlet 18 can be installed on the first housing 11. When it is necessary to clean the airflow channel 13, water can be introduced into the airflow channel 13 through the flushing inlet 18. The water flows along the airflow channel 13 and is discharged from the drain hole 131, thereby cleaning the airflow channel 13 inside the intake volute 10, which is beneficial to improving the service life of the intake volute 10.
[0055] In some embodiments, the intake housing 10 further includes a temperature sensor 4, which is disposed on the intake housing 1 and is used to detect the temperature at the inlet of the airflow channel 13.
[0056] Optionally, the inlet of the airflow channel 13 is connected to the first chamber 13a, and the temperature sensor 4 is mounted on the first housing 11. The temperature sensor 4 is used to detect the temperature at the inlet of the airflow channel 13, so that the external control module can control whether the heat source 20 is connected to the air intake pipe 3, and the flow rate and velocity of the high-temperature gas flowing therein, based on the detected temperature information.
[0057] In an embodiment of this application, an aero-engine includes an intake volute 10 as described above.
[0058] The aero-engine provided in this application embodiment has the aforementioned air intake volute 10 related structure. The air intake volute 10 provided in the above embodiments can be referred to, and it has all the beneficial effects of the aforementioned air intake volute 10, which will not be repeated here.
[0059] In some embodiments, the aero-engine further includes an intake casing, which includes an outer ring assembly and an inner ring assembly. The outer ring assembly is disposed outside the inner ring assembly. The intake housing 1 also includes a heating channel 17, at least a portion of which is disposed within a second chamber 13b. One end of the heating channel 17 is connected to the third end 33 of the bleed pipe 3 via a second air inlet 16 disposed on the second housing 12. The other end of the heating channel 17 is connected to the outer ring assembly of the intake casing, for example, to a chamber of the outer ring of the intake casing. By connecting the other end of the heating channel 17 to the outer ring assembly of the intake casing, such as a chamber of the outer ring of the intake casing, the airflow exiting the heating channel 17 can be discharged from the aero-engine through the outer ring assembly of the intake casing, which helps to balance the air pressure in the heating channel 17.
[0060] The aviation equipment provided in the embodiments of this application has all the features of the aforementioned air intake volute and / or aero-engine, and therefore also has all the beneficial effects of the aforementioned air intake volute and / or aero-engine.
[0061] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.
[0062] The above embodiments only illustrate several implementation methods of this utility model, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.
[0063] Although this application has been described with reference to preferred embodiments, various modifications can be made thereto and components can be replaced with equivalents without departing from the scope of this application. In particular, the technical features mentioned in the various embodiments can be combined in any manner, provided there is no structural conflict. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.
Claims
1. A gas inlet volute, characterized by, The intake volute includes: An air intake housing has an airflow channel, the airflow channel including a first chamber and a second chamber, the air intake housing including a drain hole communicating with the second chamber, and the first chamber communicating with the end of the second chamber opposite to the drain hole in a vertical direction; A heating housing is disposed on the air intake housing. The heating housing and the air intake housing together form a ventilation cavity. The ventilation cavity is spaced apart from the first chamber. The heating housing has a first air inlet that communicates with the ventilation cavity. An air intake pipe, the first end of which is connected to the first air inlet, and the second end of which is connected to a heat source.
2. The intake volute according to claim 1, characterized in that, The intake housing also includes a first housing and a second housing connected to each other, the first housing having the first chamber and the second housing having the second chamber.
3. The intake volute according to claim 2, characterized in that, The first air inlet is located on the side of the first housing that is away from the second housing; The first housing also includes an exhaust port, which communicates with the ventilation cavity and is located on the side of the first housing near the second housing.
4. The intake volute according to claim 2, characterized in that, Both the first housing and the second housing are semi-annular, and the first housing and the second housing together form a hollow cavity. At least a portion of the airflow channel is spaced apart from the hollow cavity and extends along the periphery of the hollow cavity. The ventilation cavity is an annular cavity that extends along a portion of the hollow cavity.
5. The intake volute according to claim 2, characterized in that, The intake housing also includes a heating channel, at least a portion of which is disposed in the second chamber. One end of the heating channel is connected to the third end of the air intake pipe through a second air inlet disposed on the second housing, and the other end of the heating channel is connected to the outer ring assembly of the intake casing.
6. The intake volute according to claim 1, characterized in that, The air intake housing includes a plurality of drain holes, which are spaced apart and communicate with the second chamber respectively.
7. The intake volute according to claim 1, characterized in that, The air intake housing also includes a flushing inlet, which is connected to the first chamber.
8. The intake volute according to claim 1, characterized in that, The intake volute also includes: A temperature sensor is disposed on the air intake housing, and the temperature sensor is used to detect the temperature at the inlet of the airflow channel.
9. An aircraft engine, characterized in that, The aero-engine includes an intake vortex as described in any one of claims 1 to 8.
10. An aviation device, characterized in that, The aviation equipment includes the aircraft engine as described in claim 9 and / or the air intake volute as described in any one of claims 1 to 8.