CN114633863B

CN114633863B - Ducted propeller of aerodynamic ship

Info

Publication number: CN114633863B
Application number: CN202210148332.9A
Authority: CN
Inventors: 陈风; 刘松; 赵玲; 徐丁丁
Original assignee: AVIC Huiyang Aviation Propeller Co Ltd
Current assignee: AVIC Huiyang Aviation Propeller Co Ltd
Priority date: 2022-02-17
Filing date: 2022-02-17
Publication date: 2024-12-17
Anticipated expiration: 2042-02-17
Also published as: CN114633863A

Abstract

The invention belongs to the field of aerodynamic design of aerodynamic ships, and relates to an aerodynamic ship duct propeller. The whole shape of the ducted propeller is rectangular blades, the blade root is circular, the blade profile from the blade root to the blade tip is formed by a plurality of ARAD airfoil shapes which are similar to the wing, the thickness is transited from thick to thin in a sliding way, a certain torsion angle is kept between each section, so that the wing cannot stall in the working process of the blade, larger aerodynamic lift force is generated, aerodynamic resistance is small, the wing profile is thinned continuously from the blade root to the blade tip through the continuous change of the thickness of the wing profile, and smooth transition is realized, namely, the strength and the rigidity of the propeller are ensured to be enough in the high-speed rotation process, strong thrust can be generated, and the high-speed navigation of an aerodynamic ship on a shoal or a water surface is ensured.

Description

Ducted propeller of aerodynamic ship

Technical Field

The invention belongs to the field of aerodynamic design of aerodynamic ships, and relates to an aerodynamic ship duct propeller.

Background

At present, the ducted propeller for the aerodynamic ship is less in application, the propeller matched with a 200 Kw-level engine is not a precedent for development, and in order to execute part of complex water patrol tasks such as shoal, sharp turns, narrow water surface and the like, the patrol duty task can be completed in all terrains of a clear water period, an ice flow period without a flood and a thin ice sealing period, and the high-performance propeller with large thrust-weight ratio (up to 25N/Kw), light weight (the total weight of the propeller is not more than 20 Kg) and low noise (not more than 90 dB) needs to be designed for the existing aerodynamic ship.

Disclosure of Invention

The invention aims to design an aerodynamic ship bypass propeller to solve the current problem.

In order to solve the technical problem, the technical scheme of the invention is as follows:

the utility model provides an aerodynamic ship ducted propeller, the ducted propeller blade has three, evenly distributed around the rotation center of the propeller blade,

The chord length of each section of the propeller blade is taken as an X axis, the chord length is taken as a Y axis and the axis of the propeller blade is taken as a Z axis, the distance from each section of the propeller blade to the rotation center of the propeller blade is r, the chord length of each section airfoil of the propeller blade is b, the included angle of each section of the propeller blade relative to the rotation plane of the blade is phi, the maximum thickness of each section of the propeller blade is c, the axis coordinate of each section of the propeller blade is (X ₀,Y₀), and the appearance, structure and size of the propeller blade meet the following conditions:

When r is 160-170 mm, b is 170-180 mm, c is 50-55 mm, phi is 30-32 degrees, and (X ₀,Y₀) is (85, -0.2) to (89,0);

when r is 280-290 mm, b is 220-230 mm, c is 30-40 mm, phi is 10-20 degrees, and (X ₀,Y₀) is (100, -2) to (110, -1);

when r is 400-500 mm, b is 200-300 mm, c is 20-30 mm, phi is 0-10 degrees, and (X ₀,Y₀) is (110,0) to (120, 1);

when r is 500-600 mm, b is 200-300 mm, c is 20-30 mm, phi is-5 to +5 degrees, and (X ₀,Y₀) is (110, -1) to (120, +1);

When r is 600-700 mm, b is 200-300 mm, c is 10-20 mm, phi is-10-0 degrees, and (X ₀,Y₀) is (110, -1) to (120, +1);

When r is 700-800 mm, b is 200-300 mm, c is 10-20 mm, phi is-10-0 degrees, and (X ₀,Y₀) is (110, -1) to (120, +1).

Further, the overall structural dimension of the blade meets the following conditions:

when r is 163-168 mm, b is 172-176 mm, c is 4-60 mm, phi is 28-35 degrees, and (X ₀,Y₀) is (80, -1) to (90,0);

When r is 283-288 mm, b is 215-217 mm, c is 35-37 mm, phi is 15-20 degrees, (X ₀,Y₀) is (105, -1) to (110,0);

When r is 400-410 mm, b is 220-230 mm, c is 22-25 mm, phi is 3-6 degrees, and (X ₀,Y₀) is (110,0) - (115,0.5);

when r is 520-540 mm, b is 200-250 mm, c is 20-25 mm, phi is-1 to +1 degrees, and (X ₀,Y₀) is (113, -0.5) to (116, +0.5);

when r is 620-650 mm, b is 220-240 mm, c is 15-17 mm, phi is-4 to-6 degrees, and (X ₀,Y₀) is (113, -0.1) to (116,0);

When r is 730-760 mm, b is 220-240 mm, c is 10-15 mm, phi is-10 to-6 degrees, and (X ₀,Y₀) is (110, -0.2) to (120, -0.1).

Preferably, the blade has the following overall structural dimensions:

When r is 165mm, b is 174mm, c is 51mm, phi is 31 DEG, (X ₀,Y₀) is (87.7, -0.16);

When r is 284 mm, b is 216mm, c is 36mm, phi is 18 DEG, (X ₀,Y₀) is (109.7, -0.35);

When r is 405mm, b is 226.7mm, c is 24.6mm, phi is 5.2 DEG, (X ₀,Y₀) is (113,0.09);

When r is 525mm, b is 230mm, c is 20.6mm, phi is 0 DEG, (X ₀,Y₀) is (115,0);

when r is 640 mm, b is 230mm, c is 16.7mm, phi is-4.5 DEG, (X ₀,Y₀) is (115, -0.05);

When r is 750mm, b is 230mm, c is 12.5mm, phi is-7 DEG, (X ₀,Y₀) is (115, -0.05).

Preferably, the blade has the following overall structural dimensions:

when r is 170mm, b is 175mm, c is 52mm, phi is 32 DEG, (X ₀,Y₀) is (88.7, -0.15);

when r is 290mm, b is 220mm, c is 37mm, phi is 19 DEG, (X ₀,Y₀) is (110, -0.5);

When r is 400mm, b is 227mm, c is 24.9mm, phi is 5.5 DEG, (X ₀,Y₀) is (114,0.10);

When r is 530mm, b is 231mm, c is 20.5mm, phi is 0.3 DEG, (X ₀,Y₀) is (118,0.5);

When r is 650mm, b is 231mm, c is 16.9mm, phi is-4.8 DEG, (X ₀,Y₀) is (115, -0.16);

When r is 750mm, b is 231mm, c is 12.8mm, phi is-7.5 DEG, (X ₀,Y₀) is (116, -0.15).

The blades of the ducted propeller adopt ARAD wing sections which are sequentially arranged from the blade root to the blade tip in a thick-to-thin sequence, and each section is in smooth transition.

The appearance of the propeller blade of the ducted propeller is rectangular, the tip of the blade is an arc, and the radius of the arc is 740-770 mm.

The material of the blades of the ducted propeller is a composite material.

The section of the duct in the ducted propeller is an NACA0012 airfoil.

The beneficial effects of the invention are as follows:

The ducted propeller adopts a three-blade design, and adopts fewer blades under the condition of obtaining the maximum thrust, and the blade materials are composite materials, so that the overall weight of the propeller is reduced as much as possible.

The invention reduces the noise of the propeller, improves the comfort level of the crew and passengers, adopts a rectangular plane shape to improve the thrust-weight ratio when the three-blade propeller is designed based on ARAD wing type design and the blade profile data is used under the provided limited power condition, so that the thrust of the propeller is greatly improved.

The total weight of the propeller is not more than 20Kg, the thrust weight ratio can reach 25N/Kw, and the noise is not more than 90dB. The aerodynamic ship speed is greater than 50Km/h.

Drawings

In order to more clearly illustrate the technical solution of the implementation of the present invention, the following description will briefly explain the drawings that need to be used in the examples of the present invention. It is evident that the drawings described below are only some embodiments of the invention and that other drawings may be obtained from these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic illustration of an overall propeller blade profile;

FIG. 2 is a schematic illustration of a single blade profile;

FIG. 3 is a parametric schematic of any airfoil section in accordance with the invention;

FIG. 4 is a three-dimensional schematic of a duct;

Fig. 5 is a schematic cross-sectional view of the bypass of fig. 4.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without making any inventive effort are intended to fall within the scope of the present invention.

Features of various aspects of embodiments of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely for a better understanding of the invention by showing examples of the invention. The present invention is not limited to any particular arrangement and method provided below, but covers any modifications, substitutions, etc. of all product constructions, methods, and the like covered without departing from the spirit of the invention.

Well-known structures and techniques have not been shown in detail in the various drawings and the following description in order not to unnecessarily obscure the present invention. The propeller blade of the present invention will be described below by taking a ducted propeller of an air patrol boat as an example:

the section of a duct in the ducted propeller is an NACA0012 wing section, and schematic diagrams are shown in figures 4 and 5;

as shown in FIG. 1, three propeller blades are made of composite materials and are uniformly distributed around the rotation center of the propeller blades, ARAD wing sections are adopted, the blade roots are sequentially arranged from the blade tips to the blade tips in a thin-thick sequence, and smooth transition is realized between each two tangent planes. The appearance of the propeller blade is rectangular, the blade tip of the propeller blade is an arc, and the radius of the arc is 750mm.

Different blade profile data are designed below, blade geometry tables are shown in tables 1 to 6.

The chord length of the propeller blade is taken as an X axis, the chord length is taken as a Y axis and the axis of the propeller blade is taken as a Z axis, the distance from each section of the propeller blade to the rotation center of the propeller blade is r, the chord length of the airfoil profile of each section of the propeller blade is b, the included angle of each section of the propeller blade relative to the rotation plane of the blade is phi, the maximum thickness of each section of the propeller blade is c, the axis coordinate of each section of the propeller blade is (X ₀,Y₀), and as shown in fig. 2 and 3, the overall dimension of the propeller blade meets the following conditions:

TABLE 1

Cut noodles	1	2	3	4	5	6
							r	165	285	405	525	645	750
b	174	216	226.7	230	230	230
							c	51	36	24.6	20.6	16.7	12.5
φ	31^O	18^O	5.2^O	0^O	-4.5^O	-7^O
							X₀	87.7	109.7	113	115	115	115
Y₀	-0.16	-0.35	0.09	0	-0.02	-0.05

TABLE 2

Cut noodles	1	2	3	4	5	6
							r	166	286	406	526	646	750
b	175	217	226.8	231	231	231
							c	50	35	24.5	20.5	16.5	12.4
φ	31.5^O	18.5^O	5.7^O	0^O	-4.6^O	-7.5^O
							X₀	87.2	109.2	112	114	114	114
Y₀	-0.14	-0.34	0.08	0	-0.03	-0.04

TABLE 3 Table 3

Cut noodles	1	2	3	4	5	6
							r	167	287	407	527	647	750
b	176	218	226.9	232	232	232
							c	49	34	24.3	20.3	16.3	12.3
φ	31.2^O	18.2^O	5.1^O	0^O	-4.8^O	-7.2O
							X₀	87.9	109.9	114	116	116	116
Y₀	-0.16	-0.35	0.09	0	-0.02	-0.05

TABLE 4 Table 4

Cut noodles	1	2	3	4	5	6
							r	168	288	408	528	648	750
b	177	219	226.0	233	233	233
							c	51	36	24.6	20.6	16.7	12.5
φ	31^O	18^O	5.2^O	0^O	-4.5^O	-7^O
							X₀	90	110	118	118	118	118
Y₀	-0.22	-0.45	0.19	0	-0.12	-0.15

TABLE 5

Cut noodles	1	2	3	4	5	6
							r	169	289	409	529	649	750
b	179	220	230	239	239	239
							c	51	36	24.6	20.6	16.7	12.5
φ	31^O	18^O	5.2^O	0^O	-4.5^O	-7^O
							X₀	89	120	123	125	125	125
Y₀	-0.20	-0.37	0.17	0	-0.22	-0.25

TABLE 6

Cut noodles	1	2	3	4	5	6
							r	170	290	410	530	650	750
b	179	220	231	235	235	235
							c	51	36	24.6	20.6	16.7	12.5
φ	30^O	17^O	4.2^O	0^O	-4.5^O	-8^O
							X₀	91	111.7	112	120	120	120
Y₀	-0.19	-0.39	0.13	0	-0.14	-0.18

In the above examples, the propeller total weight was not more than 20Kg, the thrust ratio was at least 25N/Kw (25.2N/Kw in Table 1, 25.0N/Kw in Table 2, 25.42N/Kw in Table 3, 25.15N/Kw in Table 4, 25.38N/Kw in Table 5, 25.46N/Kw in Table 6), and the noise was not more than 90dB (89.65 dB in Table 1, 89.72dB in Table 2, 89.78dB in Table 3, 89.85dB in Table 4, 89.95dB in Table 5, and 89.98dB in Table 6). The aerodynamic ship speed was greater than 50Km/h (up to 52.5Km/h for Table 1, up to 50.5Km/h for Table 2, up to 52.3Km/h for Table 3, up to 51Km/h for Table 4, up to 51.2Km/h for Table 5, and up to 50Km/h for Table 6). The blade of the present invention may also be applied to a hovercraft.

It should be noted that the above embodiments are only for illustrating the technical solution of the present invention, but the scope of the present invention is not limited thereto, and any equivalent modifications or substitutions can be easily made by those skilled in the art within the technical scope of the present invention, and these modifications or substitutions should be included in the scope of the present invention.

Claims

1. A ducted propeller of an aerodynamic ship is characterized in that three ducted propeller blades are uniformly distributed around the rotation center of the propeller blades,

When r is 160-170 mm, b is 170-180 mm, c is 50-55 mm, phi is 30-32 degrees, X ₀ is 85-89, Y ₀ is-0.2-0;

When r is 285-290 mm, b is 216-220 mm, c is 30-40 mm, phi is 10-20 degrees, X ₀ is 100-110, Y ₀ is-2 to-1;

When r is 400-500 mm, b is 200-300 mm, c is 20-30 mm, phi is 0-10 degrees, X ₀ is 110-120, Y ₀ is 0-1;

when r is 500-600 mm, b is 200-300 mm, c is 20-30 mm, phi is-5 to +5 degrees, X ₀ is 110-120, Y ₀ is-1;

when r is 600-700 mm, b is 200-300 mm, c is 10-20 mm, phi is-10-0 degrees, X ₀ is 110-120, Y ₀ is-1;

When r is 700-800 mm, b is 200-300 mm, c is 10-20 mm, phi is-10-0 degrees, X ₀ is 110-120, Y ₀ is-1.

2. The aerodynamic ship ducted propeller of claim 1, wherein the blade profile is sized to meet the following conditions:

When r is 400-410 mm, b is 220-230 mm, c is 22-25 mm, phi is 3-6 degrees, X ₀ is 110-115, Y ₀ is 0-0.5;

when r is 520-540 mm, b is 200-250 mm, c is 20-25 mm, phi is-1 to +1 degrees, X ₀ is 113-116, Y ₀ is-0.5;

When r is 620-650 mm, b is 220-240 mm, c is 15-17 mm, phi is-4 to-6 degrees, X ₀ is 113-116, Y ₀ is-0.1-0;

when r is 730-760 mm, b is 220-240 mm, c is 10-15 mm, phi is-10 to-6 degrees, X ₀ is 110-120, Y ₀ is-0.2 to-0.1.

3. The aerodynamic ship ducted propeller of claim 1, wherein the blade profile is sized as follows:

4. The aerodynamic ship ducted propeller of claim 1, wherein the blade profile is sized as follows:

5. The aerodynamic ship ducted propeller of claim 1, wherein the ducted propeller blades are ARAD airfoils, which are sequentially arranged from a blade root to a blade tip in a thickness-to-thickness order, and each tangential plane is smoothly transited.

6. The aerodynamic ship ducted propeller of claim 1, wherein the ducted propeller blade is rectangular in shape, the blade tip is circular arc, and the radius of the circular arc is 740-770 mm.

7. The aerodynamic ship ducted propeller of claim 1, wherein the ducted propeller blade material is a composite material.

8. The aerodynamic ship ducted propeller of claim 1, wherein the section of the duct in the ducted propeller is NACA0012 airfoil.