Two-side type air inlet channel structure of turboprop aircraft
By designing a two-sided air intake structure for turboprop aircraft, and adopting an integrated lip and a specific angled air intake design, the challenges of air intake structure in turboprop aircraft in terms of flow resistance and foreign object removal have been solved, achieving excellent airflow quality and foreign object removal.
Patent Information
- Application Number
- CN202511859356.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-10
- Publication Date
- 2026-01-23
AI Technical Summary
The existing turboprop aircraft's two-sided air intake structure cannot simultaneously satisfy the requirements of excellent intake airflow quality, reduced nacelle external drag, and the ability to remove foreign objects.
Design a two-sided air intake structure for a turboprop aircraft, including right and left air intake lips, inner ducts, bypass channels and outer covers. It adopts an integrated design and specific angle configuration to reduce flow resistance and remove foreign objects through the bypass channels.
It enables the fulfillment of the side-intake requirements in turboprop aircraft, reduces the impact on the external drag of the nacelle, and effectively removes foreign objects such as sand and gravel.
Smart Images
Figure CN121376181A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application belongs to the technical field of aircraft structure design, and particularly relates to a two-side air inlet structure of a turboprop aircraft. BACKGROUND
[0002] With the design evolution of the engine of the turboprop aircraft, the air inlet forms are diversified, and some engines adopt a two-side air inlet form, and therefore a main air inlet of the air inlet form needs to be designed. In order to ensure excellent air inlet flow quality, the air inlet of the turboprop aircraft usually adopts a ram air inlet, and therefore the lip, the internal flow channel and the boundary layer channel of the main part of the air inlet need to protrude from the surface of the nacelle, so that the external flow resistance of the nacelle is increased. Meanwhile, the engine of the turboprop aircraft generally requires that the air inlet has the ability to remove certain foreign matters.
[0003] In order to meet the two-side air inlet form of the engine of the turboprop aircraft, while minimizing the influence of the air inlet on the external flow resistance of the nacelle, and being able to remove certain foreign matters, a two-side air inlet structure of a turboprop aircraft is needed. SUMMARY
[0004] The application aims to provide a two-side air inlet structure of a turboprop aircraft to solve or alleviate at least one problem in the background art.
[0005] The technical scheme of the application is: a two-side air inlet structure of a turboprop aircraft, comprising:
[0006] a nacelle cover located at the rear side of the propeller cap, the nacelle cover being wrapped on the outer side of the engine to form the aerodynamic shape of the engine, and the inside of the nacelle cover being provided with an engine elbow for guiding the air inlet to the engine;
[0007] a right air inlet lip, a right air inlet duct, a right air inlet bypass channel and a right air inlet cover arranged on the right side of the nacelle cover, the right air inlet lip being arranged at the air inlet front end of the right air inlet duct, the right air inlet bypass channel being arranged at the rear side of the right air inlet duct, the right air inlet duct being in communication with the right air inlet bypass channel and the engine elbow respectively, and the right air inlet cover being arranged on the nacelle cover to wrap the right air inlet duct and the right air inlet bypass channel so as to form an aerodynamic shape on the surface of the right air inlet duct and the right air inlet bypass channel;
[0008] The left side air inlet lip, the left side air inlet inner pipe, the left side air inlet bypass and the left side air inlet cover arranged on the left side of the nacelle cover, the left side air inlet lip is arranged at the air inlet front end of the left side air inlet inner pipe, the left side air inlet bypass is arranged at the rear side of the left side air inlet inner pipe, the left side air inlet inner pipe is communicated with the left side air inlet bypass and the engine elbow respectively, and the left side air inlet cover is arranged on the nacelle cover and used for wrapping the left side air inlet inner pipe and the left side air inlet bypass to form the aerodynamic shape on the surface of the left side air inlet inner pipe and the left side air inlet bypass.
[0009] The external airflow flows into the right side air inlet inner pipe and the left side air inlet inner pipe along the right side air inlet lip and the left side air inlet lip respectively, and a part of the airflow in the right side air inlet inner pipe and the left side air inlet inner pipe flows into the engine along the engine elbow, and another part of the airflow flows out along the right side air inlet bypass and the left side air inlet bypass respectively.
[0010] Preferably, the right side air inlet lip and the right side air inlet inner pipe are designed in an integrated manner; and / or
[0011] The left side air inlet lip and the left side air inlet inner pipe are designed in an integrated manner.
[0012] Preferably, the right side air inlet lip and the right side air inlet inner pipe are both in a strip structure, and the curved shape of the right side air inlet lip and the right side air inlet inner pipe is consistent with the intersection shape formed by the plane and the nacelle cover.
[0013] The left side air inlet lip and the left side air inlet inner pipe are both in a strip structure, and the curved shape of the left side air inlet lip and the left side air inlet inner pipe is consistent with the intersection shape formed by the plane and the nacelle cover.
[0014] Preferably, the right side air inlet bypass and the left side air inlet bypass both have a first angle with the direction of the external airflow in the lateral direction, and the first angle is configured to be 10° to 45°.
[0015] Preferably, the right side air inlet bypass and the left side air inlet bypass both have a second angle with the direction of the external airflow in the radial direction, and the second angle is configured to be 30° to 50°.
[0016] Preferably, the right side air inlet lip and the left side air inlet lip, the right side air inlet inner pipe and the left side air inlet inner pipe, the right side air inlet bypass and the left side air inlet bypass and the right side air inlet cover and the left side air inlet cover are respectively symmetric about the radial center of the nacelle cover.
[0017] This application provides an air intake structure for turboprop aircraft that can meet the requirements of side-mounted air intakes. By utilizing a specific lip shape, the air intake can minimize the impact of external airflow resistance on the nacelle, and by using a bypass channel to remove foreign objects such as sand and gravel from the external airflow, it can achieve the ability to remove a certain amount of foreign objects. Attached Figure Description
[0018] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.
[0019] Fig. 1 This is a schematic diagram of the two-sided air intake structure of the turboprop aircraft of this application.
[0020] Fig. 2 This is a front view of the side-mounted air intake structure of the turboprop aircraft described in this application.
[0021] Fig. 3 This is a schematic diagram of the installation structure of the left intake lip and the inner pipe of the left intake in this application. Detailed Implementation
[0022] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.
[0023] This application provides a two-sided air intake structure for a turboprop aircraft, which provides the required air for the turboprop aircraft engine, meets the requirements of two-sided air intake for the engine, reduces the impact on external drag characteristics, and has the ability to remove a certain amount of foreign matter.
[0024] like Figs. 1-3 As shown, the turboprop aircraft dual-side air intake structure provided in this application includes: a right air intake lip 31, a left air intake lip 32, a right air intake inner duct 41, a left air intake inner duct 42, a right air intake side passage 51, a left air intake side passage 52, a right air intake outer cover 61, a left air intake outer cover 62, a nacelle outer cover 7, and an engine bend 8.
[0025] The propeller 2 is mounted on the propeller cap 1 and rotates around the axis of the propeller cap 1. The propeller cap 1 is located in front of the nacelle cover 7, which wraps around the outside of the engine (outer side) to form the aerodynamic shape of the engine. The engine bend 8 is located inside the nacelle cover 7 to guide the intake air into the engine. In some embodiments of this application, the engine bend 8 has a herringbone structure, with two inlets connected to the right intake duct 41 and the left intake duct 42 respectively, and one outlet connected to the engine inlet, thereby transmitting the airflow flowing into the right intake duct 41 and the left intake duct 42 into the engine.
[0026] The right intake lip 31, the right intake duct 41, the right bypass duct 51 and the right intake cover 61 are arranged on the right side of the nacelle cover 7, the right intake lip 31 is arranged at the air intake front end of the right intake duct 41, the right bypass duct 51 is arranged at the rear side of the right intake duct 41, and the right intake duct 41 is communicated with the right bypass duct 51 and the engine elbow 8 respectively. The right intake cover 61 is arranged on the nacelle cover 7 and is used to wrap the right intake duct 41 and the right bypass duct 51, so as to form a aerodynamic shape on the surface of the right intake duct 41 and the right bypass duct 51.
[0027] Similarly, the left intake lip 32, the left intake duct 42, the left bypass duct 52 and the left intake cover 62 are arranged on the left side of the nacelle cover 7, the left intake lip 32 is arranged at the air intake front end of the left intake duct 42, the left bypass duct 52 is arranged at the rear side of the left intake duct 42, and the left intake duct 42 is communicated with the left bypass duct 52 and the engine elbow 8 respectively. The left intake cover 62 is arranged on the nacelle cover 7 and is used to wrap the left intake duct 42 and the left bypass duct 52, so as to form a aerodynamic shape on the surface of the left intake duct 42 and the left bypass duct 52.
[0028] When the turboprop aircraft is working, the external airflow (shown by the dotted arrow) passes through the propeller 2 and then flows into the right intake duct 41 and the left intake duct 42 along the right intake lip 31 and the left intake lip 32 respectively, part of the airflow in the right intake duct 41 and the left intake duct 42 flows into the engine along the engine elbow 8, and the other part of the airflow flows out along the right bypass duct 51 and the left bypass duct 52 respectively, so that the foreign matters such as sand in the external airflow can be removed.
[0029] In some embodiments of the present application, the right intake lip 31 or the left intake lip 32 can be designed in an integrated manner with the corresponding intake duct, so as to avoid the joint between the lip and the duct and affect the aerodynamic effect. For example, the right intake lip 31 and the right intake duct 41 can be formed in an integrated structure by means of integrated extrusion molding.
[0030] In the preferred embodiment of the present application, the right intake lip 31 and the left intake lip 32, the right intake duct 41 and the left intake duct 42, the right bypass duct 51 and the left bypass duct 52, and the right intake cover 61 and the left intake cover 62 are respectively symmetrical about the radial center plane A of the nacelle cover 7.
[0031] Further, the right side air inlet lip 31 and the right side air inlet inner duct 41 in the present application are both strip-shaped structures, and the curved shapes of the right side air inlet lip 31 and the right side air inlet inner duct 41 are consistent with the intersection shapes formed by the planes where the right side air inlet lip 31 and the right side air inlet inner duct 41 are located and the nacelle outer cover 7, i.e., the center lines of the strip-shaped structures of the right side air inlet lip 31 and the right side air inlet inner duct 41 are curved to the outside (left side) of the nacelle outer cover 7. Fig. 2 Similarly, the left side air inlet lip 32 and the left side air inlet inner duct 42 are both strip-shaped structures, and the curved shapes of the left side air inlet lip 32 and the left side air inlet inner duct 42 are consistent with the intersection shapes formed by the planes where the left side air inlet lip 32 and the left side air inlet inner duct 42 are located and the nacelle outer cover 7, i.e., the center lines of the strip-shaped structures of the left side air inlet lip 32 and the left side air inlet inner duct 42 are curved to the outside (right side) of the nacelle outer cover 7. Fig. 2
[0032] In the preferred embodiment of the present application, the right side air inlet bypass duct 51 has a first angle in the lateral direction with respect to the direction of the external incoming flow, and the first angle a is configured to be 10° to 45°. Similarly, the left side air inlet bypass duct 52 has a first angle in the lateral direction with respect to the direction of the external incoming flow, and the first angle a is configured to be 10° to 45°.
[0033] Further, the right side air inlet bypass duct 51 has a second angle in the radial direction with respect to the direction of the external incoming flow, and the second angle b is configured to be 30° to 50°. Similarly, the left side air inlet bypass duct 52 has a second angle in the radial direction with respect to the direction of the external incoming flow, and the second angle b is configured to be 30° to 50°.
[0034] The present application provides an air inlet structure for turboprop aircrafts that can meet the air inlet requirements of both sides, and uses specific lip shapes to minimize the influence of the air inlet on the outflow resistance of the nacelle, and uses bypass ducts to remove foreign matter such as sand and stones in the external incoming flow, thereby achieving the ability to remove certain foreign matter.
[0035] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, and any changes or replacements that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. A twin-aisle turbofan aircraft with a two-sided inlet structure, characterized in that, The application relates to a nacelle outer cover (7) located at the back side of a propeller cap (1), which is wrapped outside the engine to form the aerodynamic shape of the engine, and an engine elbow pipe (8) is arranged inside the nacelle outer cover (7) to guide the air intake into the engine. A right-side air intake lip (31), a right-side air intake inner pipe (41), a right-side air intake bypass (51) and a right-side air intake outer cover (61) are arranged on the right side of the nacelle outer cover (7), the right-side air intake lip (31) is arranged at the air intake front end of the right-side air intake inner pipe (41), the right-side air intake bypass (51) is arranged at the back side of the right-side air intake inner pipe (41), the right-side air intake inner pipe (41) is communicated with the right-side air intake bypass (51) and the engine elbow pipe (8) respectively, and the right-side air intake outer cover (61) is arranged on the nacelle outer cover (7) to wrap the right-side air intake inner pipe (41) and the right-side air intake bypass (51) so as to form the aerodynamic shape on the surfaces of the right-side air intake inner pipe (41) and the right-side air intake bypass (51). A left-side air intake lip (32), a left-side air intake inner pipe (42), a left-side air intake bypass (52) and a left-side air intake outer cover (62) are arranged on the left side of the nacelle outer cover (7), the left-side air intake lip (32) is arranged at the air intake front end of the left-side air intake inner pipe (42), the left-side air intake bypass (52) is arranged at the back side of the left-side air intake inner pipe (42), the left-side air intake inner pipe (42) is communicated with the left-side air intake bypass (52) and the engine elbow pipe (8) respectively, and the left-side air intake outer cover (62) is arranged on the nacelle outer cover (7) to wrap the left-side air intake inner pipe (42) and the left-side air intake bypass (52) so as to form the aerodynamic shape on the surfaces of the left-side air intake inner pipe (42) and the left-side air intake bypass (52). Air flows into the right-side air intake inner pipe (41) and the left-side air intake inner pipe (42) along the right-side air intake lip (31) and the left-side air intake lip (32) respectively, and part of the air in the right-side air intake inner pipe (41) and the left-side air intake inner pipe (42) flows into the engine along the engine elbow pipe (8), and the other part of the air flows out along the right-side air intake bypass (51) and the left-side air intake bypass (52) respectively. The right-side air intake lip (31) and the right-side air intake inner pipe (41) are designed in an integrated mode; and / or 2. The twin-banked turboprop aircraft structure of claim 1, wherein, The left-side air intake lip (32) and the left-side air intake inner pipe (42) are designed in an integrated mode. The right-side air intake lip (31) and the right-side air intake inner pipe (41) are both strip-shaped structures, and the bending shapes of the right-side air intake lip (31) and the right-side air intake inner pipe (41) are consistent with the intersection shapes formed by the planes and the nacelle outer cover (7); and / or 3. The twin-banked turboprop aircraft air inlet structure as claimed in claim 1, characterized in that, The left-side air intake lip (32) and the left-side air intake inner pipe (42) are both strip-shaped structures, and the bending shapes of the left-side air intake lip (32) and the left-side air intake inner pipe (42) are consistent with the intersection shapes formed by the planes and the nacelle outer cover (7). The left side air inlet channel lip (32) and the left side air inlet channel inner pipeline (42) are both strip-shaped structures, and the curved shapes of the left side air inlet channel lip (32) and the left side air inlet channel inner pipeline (42) are consistent with the intersection shapes formed by the planes and the nacelle outer cover (7).
4. The twin-banked turboprop aircraft air inlet structure as claimed in claim 1, characterized in that, The right side air inlet channel bypass (51) and the left side air inlet channel bypass (52) both have a first angle with the direction of the external flow in the lateral direction, and the first angle is configured to be 10°-45°.
5. The twin-banked turboprop aircraft structure of claim 1, wherein, The right side air inlet channel bypass (51) and the left side air inlet channel bypass (52) both have a second angle with the direction of the external flow in the radial direction, and the second angle is configured to be 30°-50°.
6. The two-sided inlet structure of a turboprop aircraft as claimed in any one of claims 1 to 5, characterized in that The right side air inlet channel lip (31) and the left side air inlet channel lip (32), the right side air inlet channel inner pipeline (41) and the left side air inlet channel inner pipeline (42), the right side air inlet channel bypass (51) and the left side air inlet channel bypass (52), and the right side air inlet channel outer cover (61) and the left side air inlet channel outer cover (62) are respectively symmetric about the radial center plane of the nacelle outer cover (7).