CN101181929A - Selection designing method for marine main controllable pitch propeller device - Google Patents

Abstract

The invention provides a type selection design method of a main controllable pitch propeller used for a ship, belonging to ship design and manufacture field. According to the existing parameters of a hull, a host machine and a gearbox, the diameter H of a hub is selected; furthermore, the blade diameter D, the blade area ratio EAR, the pitch ratio P/D, the efficiency Eta, and the blade number z of the controllable pitch propeller are determined according to the maps of fixed pitch propeller series; the mass and the movement inertia of the controllable pitch propeller blade are determined according to experimental formula; strength checking and bearing capability checking to the hub are carried out, and the application performance requirement of the controllable pitch propeller is well met. The invention obtains the type selection design proposal, with the advantages of good safety and reliability, small design fund investment, simplified program, short design period, good system performance, convenient data processing, convenient management with computers, exact and reliable data, smaller error compared with post-design, little changes on the parameters determined by the type selection design in the process of the post-technology design of the controllable pitch propeller, convenient adjustment, thus simplifying the post-design flow, shortening the period and improving the efficiency.

Description

The selection designing method of marine main controllable pitch propeller device

Technical field

The present invention relates to a kind of design method of propeller, relate in particular to a kind of marine main controllable pitch propeller device selection designing method in earlier stage.

Background technology

Boats and ships are promoted mainly adjustable pitch propeller, below all abbreviate " tuning for Controllable Pitch Propeller " as, as the power system of boats and ships, its early stage Selection and Design purpose be according to hull, the parameter of main frame and gear case is determined size factor, inertia key element, load-carrying capacity and the hydraulic system parameters of tuning for Controllable Pitch Propeller.For the general design on naval vessel, the Cost Offer of tuning for Controllable Pitch Propeller and the later stage design of tuning for Controllable Pitch Propeller provide the basic data support.Early stage, Selection and Design was that we carry out the tuning for Controllable Pitch Propeller later stage design-calculated first step.Present domestic fixed pitch propeller design-calculated method mainly is to adopt the collection of illustrative plates design method, promptly determines the optimum diameter of screw propeller according to the serial collection of illustrative plates of standard, pitch ratio, parameters such as disk ratio and efficient.The collection of illustrative plates design method is to test all kinds of collection of illustrative plates that are depicted as special use according to the spacious water system row of model propeller to design.Design not only convenience of calculation of spacing oar with atlas calculation, be easy to be grasped by people, and suitable as selecting collection of illustrative plates for use, and its result is also comparatively satisfied, is to use wider a kind of method of designing at present.Because the collection of illustrative plates of screw propeller can obtain easily, therefore, also wishes to adopt the collection of illustrative plates design method when the tuning for Controllable Pitch Propeller Selection and Design.At present, domestic also do not have a complete tuning for Controllable Pitch Propeller selection designing method.Offshore company is when the design tuning for Controllable Pitch Propeller, the general methods such as lifting surface method and panel method that adopt, lifting surface method and Design by Surface Panel Method are more advanced screw propeller design technology, they are from the hydrodynamic property of the screw propeller design tuning for Controllable Pitch Propeller of starting with, be equipped with model test then, design is revised to theory, thereby can obtain the screw propeller unit design scheme of function admirable.But the input ratio of above method is bigger, the process of the test complexity, and the cycle is longer, is not suitable for the domestic tuning for Controllable Pitch Propeller Selection and Design stage in early stage.

Summary of the invention

The present invention mainly is that the solution prior art can't have high input by screw propeller collection of illustrative plates design tuning for Controllable Pitch Propeller with by the hydrodynamic property design, tests technical matterss such as complicated, design cycle length, and a kind of selection designing method of marine main controllable pitch propeller device is provided.This method can be by the screw propeller collection of illustrative plates, and is convenient and swift, finish the Selection and Design of tuning for Controllable Pitch Propeller at low cost.

Above-mentioned technical matters of the present invention is mainly solved by following technical proposals: the selection designing method of marine main controllable pitch propeller device may further comprise the steps successively:

A. size will be counted definitely, according to the parameter of hull, main frame and gear case, selects hub diameter, and determines the diameter of propeller blade of tuning for Controllable Pitch Propeller, disk ratio, pitch ratio, efficient, number of blade according to the sequential propeller sequential collection of illustrative plates;

B. the inertia key element is determined, determines the quality and the rotor inertia of tuning for Controllable Pitch Propeller blade according to empirical equation:

The blade quality $G_b=k_G\×\frac{D^3\×\mathrm{EAR}\×\frac{t_0}{D}\×\mathrm{\δ}}{z},\mathrm{kg}$

In the formula,

k _GBe coefficient, $k_G=\left\{\begin{array}{cc}228& D\≤3.0m\\ 222& D>3.0m\end{array}\right.$

t ₀/ D is the thickness diameter ratio at oar axle place, $t_0/D=\left\{\begin{array}{cc}0.055& z=3\\ 0.05& z=4\\ 0.045& z=5\end{array}\right.$

δ, blade density of material (kg/dm ³)

The blade rotor inertia $J=k_{G{D}^2}\×\frac{D^5\×\mathrm{EAR}\×(\frac{t_0}{D}+3\×\frac{t_1}{D})\×\mathrm{\δ}}{4*z},{\mathrm{kgm}}^2$

In the formula,

$k_{G{D}^2}=\left\{\begin{array}{cc}65& D\≤3.0m\\ 61& D>3.0m\end{array}\right.$

t ₁/ D is the thickness diameter ratio that leaf is located slightly, t ₁/ D=0.003+0.004/D;

C. propeller hub strength check, the repeating step A-C if propeller hub intensity does not meet the demands;

D. load-carrying capacity is checked, the repeating step A-D if load-carrying capacity does not meet the demands;

E. the tuning for Controllable Pitch Propeller hydraulic system parameters is determined, according to the tuning for Controllable Pitch Propeller design regulation, determines cylinder diameter, system pressure, flow and power of motor;

F. the tuning for Controllable Pitch Propeller axle is determining of diameter, according to the tuning for Controllable Pitch Propeller design regulation, determines tuning for Controllable Pitch Propeller main shaft diameter;

G. export the result of tuning for Controllable Pitch Propeller conceptual design in early stage.

In the steps A of the present invention, behind the selection hub diameter, press the sequential propeller sequential collection of illustrative plates, by the disk ratio of selecting for use from small to large in proper order, determine not take place disk ratio, diameter of propeller blade, pitch ratio and the efficient of cavitation successively,

Its constraint condition is:

When the check process that the present invention can also work as step C and step D all once meets the demands, then return steps A, reduce hub diameter, continue step B-D, when the check process of step C or step D does not meet the demands, adopt again among last step A-D and satisfy the size factor and the inertia key element of checking requirement, continue step e-F.

Total stress among the step C of the present invention on the blade should be less than the permissible stress of blade bolt.

In the design of tuning for Controllable Pitch Propeller, the design strength of blade is greater than the blade bolt, and the design strength of propeller hub is greater than blade, and the design strength of prop shaft is greater than propeller hub, and this principle of design is called " pyramid intensity ".So in fact concept phase, the check of propeller hub intensity are exactly the strength check that carries out the blade bolt, transverse force and centnifugal force that thrust that is subjected to according to blade and moment of torsion produce calculate the stress of blade bolt, should not surpass the permissible tensile stress of bolt.

Among the step D of the present invention, load-carrying capacity is checked to checking the load-carrying capacity ratio, and load-carrying capacity compares k _p=K _D/ K _B＞1.5,

In the formula: K _BBe blade cross section, 0.35R place load-carrying capacity, R=D/2, K _DBe the propeller hub load-carrying capacity;

$K_B=\frac{W_{0.35}\×{\mathrm{\σ}}_S\×{10}^{-3}}{R_L-R_B}$

W _0.35Be the composite bending modulus in blade cross section, 0.35R place, W _0.35=0.0448 * C _0.35* (t _0.35) ²/ 0.47

C _0.35Be 0.35R place blade chord length, C _0.35=1.973 * EAR * D/z

t _0.35Be 0.35R place blade thickness, t _0.35=(0.0433-0.00325 * z) * D

Z is a number of blade

σ _sYield point for the blade material

R _L＝0.9R

R _B＝0.35R

$K_D=\frac{k\×{d_H}^3}{{10}^2\×(R_L-L_2)}$

K is a coefficient,

d _HBe hub diameter

L ₂Be the distance of propeller shank end face of flange to propeller center.

Calculate load-carrying capacity than the time, the load-carrying capacity ratio of fitness for purpose tuning for Controllable Pitch Propeller should be greater than 1.5, so exactly in order to guarantee that load on the blade in safe range, meets " pyramid intensity " principle of design.

Advantage of the present invention and beneficial effect are: 1. carry out the Selection and Design in early stage of tuning for Controllable Pitch Propeller in conjunction with the basic data in the sequential propeller sequential collection of illustrative plates, need not spend a large amount of funds purchase advanced design schemes or carry out the advanced design test, and the simplification of designing program, fund input is few.Design cycle shorter, systematicness is good, datumization is handled convenient, is convenient to computer management.By the software that this method is made, can in 30 minutes, finish the Selection and Design of a tuning for Controllable Pitch Propeller, even on the basis of grasp method,, can finish the Selection and Design of tuning for Controllable Pitch Propeller by hand according to the data bank of being set up.Early stage the Selection and Design scheme data accurately and reliably.By checking propeller hub intensity and load-carrying capacity, guarantee safety of tuning for Controllable Pitch Propeller design-calculated and economy, satisfied the requirement of tuning for Controllable Pitch Propeller in-use performance preferably.4. adopt method of designing of the present invention to adopt the design regulation of tuning for Controllable Pitch Propeller morely, refinement simultaneously the constraint condition at key Design position, to obtain the preferable advanced design scheme of safety and reliability, less with later stage design-calculated error, in the later stage of tuning for Controllable Pitch Propeller technical design process to early stage Selection and Design the change of definite parameter few, easy to adjust, the later stage design cycle is simplified, cycle shortens, and efficient improves.

Description of drawings

Fig. 1 is the inventive method principle of design scheme drawing.

The specific embodiment

Below by embodiment, and accompanying drawings, technical scheme of the present invention is described in further detail.

Referring to Fig. 1,

The selection designing method of marine main controllable pitch propeller device of the present invention may further comprise the steps successively:

A. size will be counted definitely, according to the parameter of hull, main frame and gear case, selects hub diameter d _H, and determine the diameter of propeller blade D of tuning for Controllable Pitch Propeller, disk ratio EAR, pitch ratio P/D, efficiency eta, number of blade z according to the sequential propeller sequential collection of illustrative plates;

B. the inertia key element is determined, determines the quality and the rotor inertia of tuning for Controllable Pitch Propeller blade according to empirical equation:

The blade quality $G_b=k_G\×\frac{D^3\×\mathrm{EAR}\×\frac{t_0}{D}\×\mathrm{\δ}}{z},\mathrm{kg}$

In the formula,

k _GBe coefficient, $k_G=\left\{\begin{array}{cc}228& D\≤3.0m\\ 222& D>3.0m\end{array}\right.$

t ₀/ D is the thickness diameter ratio at oar axle place, $t_0/D=\left\{\begin{array}{cc}0.055& z=3\\ 0.05& z=4\\ 0.045& z=5\end{array}\right.$

δ, blade density of material (kg/dm ³)

The blade rotor inertia $J=k_{G{D}^2}\×\frac{D^5\×\mathrm{EAR}\×(\frac{t_0}{D}+3\×\frac{t_1}{D})\×\mathrm{\δ}}{4*z},{\mathrm{kgm}}^2$

In the formula,

$k_{G{D}^2}=\begin{array}{c}\left\{\begin{array}{cc}65& D\≤3.0m\\ 61& D>3.0m\end{array}\right.\end{array}$

t ₁/ D is the thickness diameter ratio that leaf is located slightly, t ₁/ D=0.003+0.004/D;

C. propeller hub strength check, the repeating step A-C if propeller hub intensity does not meet the demands;

D. load-carrying capacity is checked, the repeating step A-D if load-carrying capacity does not meet the demands;

E. the tuning for Controllable Pitch Propeller hydraulic system parameters is determined, according to the tuning for Controllable Pitch Propeller design regulation, determines cylinder diameter, system pressure P, flow Q and power of motor;

F. the tuning for Controllable Pitch Propeller axle is determining of diameter, according to the tuning for Controllable Pitch Propeller design regulation, determines tuning for Controllable Pitch Propeller main shaft diameter d _f

G. export the result of tuning for Controllable Pitch Propeller conceptual design in early stage.

In the steps A, select hub diameter d _HAfter, press the sequential propeller sequential collection of illustrative plates, successively by the disk ratio EAR that selects for use ₁From small to large in proper order, determine not take place disk ratio EAR, diameter of propeller blade D, pitch ratio P/D and the efficiency eta of cavitation,

Its constraint condition is:

When the check process of step C and step D all once meets the demands, then return steps A, reduce hub diameter d _H, continue step B-D, when the check process of step C or step D does not meet the demands, adopt again among last step A-D and satisfy the size factor and the inertia key element of checking requirement, continue step e-F.

Total stress σ among the step C on the blade _TotShould be less than the permissible stress of blade bolt.

Among the described step D, load-carrying capacity is checked to checking load-carrying capacity and is compared k _p, load-carrying capacity compares k _p=K _D/ K _B＞1.5,

In the formula: K _BBe blade cross section, 0.35R place load-carrying capacity, R=D/2, K _DBe the propeller hub load-carrying capacity;

$K_B=\frac{W_{0.35}\×{\mathrm{\σ}}_S\×{10}^{-3}}{R_L-R_B}$

W _0.35Be the composite bending modulus in blade cross section, 0.35R place, W _0.35=0.0448 * C _0.35* (t _0.35) ²/ 0.47

C _0.35Be 0.35R place blade chord length, C _0.35=1.973 * EAR * D/z

t _0.35Be 0.35R place blade thickness, t _0.35=(0.0433-0.00325 * z) * D

Z is a number of blade

σ _sYield point for the blade material

R _L＝0.9R

R _B＝0.35R

$K_D=\frac{k\×{d_H}^3}{{10}^2\×(R_L-L_2)}$

K is a coefficient,

d _HBe hub diameter

L ₂Be the distance of propeller shank end face of flange to propeller center.

Main controllable pitch propeller device with certain warship is an example below, adopts screw propeller B _p-δ collection of illustrative plates carries out the tuning for Controllable Pitch Propeller Selection and Design in conjunction with China Classification Society " steel seagoing vessel classification rules " (2006), and the detailed process of Selection and Design of the present invention is described:

Ship's classification: CCS

Ice level: do not have

Designed waterline length L _WL: 142.0m

Designed draft: 6.1m

Molded breadth B:19.0m

Displacement: 9650t

Waterplane area coefficient C _WP: 0.757

Midship section area factor C _M: 0.955

Block coefficient Cb:0.569

Propelling form: the two oars of two-shipper

Every main engine power/rotating speed

Applying working condition (CSR) kW/rpm 7480/520

Standard duty (MCR) kW/rpm 8800/520

Overload operating mode (OR, 12h allows 1h): kW/rpm 9680/537

Every oar power and rotating speed:

Blade design point operating mode: kW/rpm 7106/179.3

Blade peak load operating mode: kW/rpm 8360/179.3

Check operating mode: kW/rpm 9195/185

Wake coefficient: 0.11

The speed of a ship or plane (design conditions): 22kn

1.1 known conditions

Number of blade z	Main engine power P E， kW	Propeller power P D，kW	Wake coefficient ω	Allow diameter D max， m	Ship's speed V, kn	Immersed depth h, m	Propeller speed N, r/min	Screw propeller quantity
									4	7480	7160	0.11	4.2	22	4.0	179.3	2

1.2 the blade key element is determined

1.2.1 size factor

Preliminary election hub diameter d _H=1.210m

Handle according to constraint condition, obtain optimal result:

D	EAR 0	P/D	η 0
				4.20m	0.542	1.121	0.686

1.2.2 inertia key element

Single paddle calculates:

The blade quality $G_b=k_G\×\frac{D^3\×\mathrm{EAR}\×\frac{t_0}{D}\×\mathrm{\δ}}{z}=1132.46\mathrm{kg}$

Wherein,

k _GBe coefficient, $k_G=\left\{\begin{array}{cc}228& D\≤3.0m\\ 222& D>3.0m\end{array}\right.$

t ₀/ D is the thickness diameter ratio at oar axle place, $t_0/D=\left\{\begin{array}{cc}0.055& z=3\\ 0.05& z=4\\ 0.045& z=5\end{array}\right.$

The density δ of 3 grades of nickel aluminium bronze materials is 7.60kg/dm ³

The blade rotor inertia $J=k_{G{D}^2}\×\frac{D^5\×\mathrm{EAR}\×(\frac{t_0}{D}+3\×\frac{t_1}{D})\×\mathrm{\δ}}{4*z}=1277.93{\mathrm{kgm}}^2$

Wherein, $k_{G{D}^2}=\left\{\begin{array}{cc}65& D\≤3.0m\\ 61& D>3.0m\end{array}\right.$

The thickness diameter that leaf is located slightly compares t ₁/ D=0.003+0.004/D

1.3 propeller hub strength check

1.3.1 bending force on the blade and flexure stress

During free running, the thrust of each blade:

$\frac{S}{z}=\frac{P_D\×{\mathrm{\η}}_0}{z\×0.514443\×V_A}=121.91,\mathrm{kN}=12426.77\mathrm{kgf}$

Wherein, P _D, kW

V _A，kn

The transverse load of each blade:

$\frac{T}{z}=\frac{P_D}{N\×\frac{2\mathrm{\π}}{60}\×L_1\×z}=64.85,\mathrm{kN}=6610.86\mathrm{kgf}$

Wherein, P _D, kW

L ₁, transverse load is made a concerted effort T to the distance of propeller center, 1.47m

Make a concerted effort: $R_S=\sqrt{{\left(\frac{S}{z}\right)}^2+{\left(\frac{T}{z}\right)}^2}=14075.79\mathrm{kgf}$

Flexure stress: ${\mathrm{\σ}}_{\mathrm{bS}}=\frac{R_S\×(L_1-L_2)}{W_b}=345.90\mathrm{kgf}/{\mathrm{cm}}^2$

Wherein, the blade end face of flange is to the distance L of propeller center ₂=46cm

The bending modulus W of blade bolt _b=4110cm ³

1.3.2 centnifugal force and centrifugal stress

Centnifugal force: $C_b=\frac{G_b\×T_{\mathrm{pb}}}{9.81}\×{\left(\frac{\mathrm{\π}\×N}{30}\right)}^2=36670.51\mathrm{kgf}$

Wherein, G _b, blade quality, kg

T _Pb, the blade center of gravity arrives the distance of propeller center, the 1.197m centrifugal stress:

${\mathrm{\σ}}_b=\frac{C_b}{S_b}=156.28\mathrm{kgf}/{\mathrm{cm}}^2$

Wherein, S _b, the cross-sectional area sum of blade bolt, 235cm ²

Total stress

σ _tot＝σ _bs+σ _d＝502.18kgf/cm ²

Be less than the permissible stress of bolt: 640kgf/cm ²

1.4 load-carrying capacity ratio

1.4.10.35R locate blade cross section load-carrying capacity

0.35R locating the blade chord length calculates: C _0.35=1.973*EAR*D/z=1122.8mm

0.35R locating blade thickness calculates: t _0.35=(0.0433-0.00325*z) * D=127.26mm

0.35R locating the composite bending modulus in blade cross section calculates: W _0.35=0.0448*C _0.35* (t _0.35) ²/ 0.47=1733270.7mm ³

$K_B=\frac{W_{0.35}\×{\mathrm{\σ}}_S\×{10}^{-3}}{R_L-R_B}=36.0T$

Wherein,

σ _s, the yield point of blade material, such as, 3 grades of nickel aluminium bronze material σ _sBe 24kgf/mm ²

R _L=0.9R mm (R is the radius of screw propeller)

R _B＝0.35R mm

1.4.2 propeller hub load-carrying capacity

$K_D=\frac{k\×{d_H}^3}{{10}^2\×(R_L-L_2)}=141.23T$

Wherein,

d _H, hub diameter, cm

The blade root end face of flange is to the distance L of propeller center ₂=46cm

1.4.3 check

Load-carrying capacity compares k _p=K _D/ K _B=3.9

k _p＞1.5 can meet design requirement

1.5 hydraulic system parameters is calculated

Load size and selected cylinder diameter are determined the pressure P=5MPa of hydraulic efficiency pressure system as requested, determine flow Q=296L/min according to the requirement of displacement time again, according to pressure, flow, factors such as the Volumetric efficiency of pump and mechanical efficiency determine that power of motor is 35.0kw.

1.6 axle system

1.6.1 the basic diameter of axle

Basic diameter=420mm by standard reference axis system.

1.7 Selection and Design is mainly exported the result:

Diameter of propeller: 4200mm

Blade quantity: 4

Propeller hub specifications and models: WP 121/4-D, d _H=1210mm

Pitch ratio: 1.121

Disk ratio: 0.542

Efficient: 0.686

One piece blade quality: about 1132.46kg

The propeller hub assembly of band blade: about 10634.82kg

One piece blade rotor inertia (in air): about 1277.93kgm ²

Flow rate of hydraulic system: 296L/min

Hydraulic system pressure: 5MPa

Power of motor: 35.0kW

The basic diameter of propeller shafting: 420mm.

The inventive method tuning for Controllable Pitch Propeller convenient, fast, design cost is lower.Result by above method of designing output provides than the accurate data parameter for the general design on naval vessel, the Cost Offer of tuning for Controllable Pitch Propeller and the later stage design of tuning for Controllable Pitch Propeller.Less to the change of Selection and Design parameter in the later stage design, generally only relate to modification to the blade curved surface, the later stage design cycle is simplified, the cycle shortens, and efficient improves.

Claims (5)

1. the selection designing method of marine main controllable pitch propeller device is characterized in that: may further comprise the steps successively:

A. size will be counted definitely, according to the parameter of hull, main frame and gear case, selects hub diameter (d _H), and determine the diameter of propeller blade (D) of tuning for Controllable Pitch Propeller, disk ratio (EAR), pitch ratio (P/D), efficient (η), number of blade (z) according to the sequential propeller sequential collection of illustrative plates;

B. the inertia key element is determined, determines the quality and the rotor inertia of tuning for Controllable Pitch Propeller blade according to empirical equation:

The blade quality $G_b=k_G\×\frac{D^3\×\mathrm{EAR}\×\frac{t_0}{D}\×\mathrm{\δ}}{z}\mathrm{kg}$

In the formula,

k _GBe coefficient, $k_G=\left\{\begin{array}{cc}228& D\≤3.0m\\ 222& D>3.0m\end{array}\right.$

t ₀/ D is the thickness diameter ratio at oar axle place, $t_0/D=\left\{\begin{array}{cc}0.055& z=3\\ 0.05& z=4\\ 0.045& z=5\end{array}\right.$

δ, blade density of material (kg/dm ³)

The blade rotor inertia $J=k_{G{D}^2}\×\frac{D^5\×\mathrm{EAR}\×(\frac{t_0}{D}+3\×\frac{t_1}{D})\×\mathrm{\δ}}{4*z}{\mathrm{kgm}}^2$

In the formula,

$k_{G{D}^2}=\left\{\begin{array}{cc}65& D\≤3.0m\\ 61& D>3.0m\end{array}\right.$

t ₁/ D is the thickness diameter ratio that leaf is located slightly, t ₁/ D=0.003+0.004/D;

C. propeller hub strength check, the repeating step A-C if propeller hub intensity does not meet the demands;

D. load-carrying capacity is checked, the repeating step A-D if load-carrying capacity does not meet the demands;

E. the tuning for Controllable Pitch Propeller hydraulic system parameters is determined, according to the tuning for Controllable Pitch Propeller design regulation, determines cylinder diameter, system pressure (P), flow (Q) and power of motor;

F. the tuning for Controllable Pitch Propeller axle is determining of diameter, according to the tuning for Controllable Pitch Propeller design regulation, determines tuning for Controllable Pitch Propeller main shaft diameter (d _f);

G. export the result of tuning for Controllable Pitch Propeller conceptual design in early stage.

2. the selection designing method of marine main controllable pitch propeller device according to claim 1 is characterized in that: in the steps A, select hub diameter (d _H) after, press the sequential propeller sequential collection of illustrative plates, successively by the disk ratio (EAR that selects for use ₁) from small to large in proper order, determine not take place disk ratio (EAR), diameter of propeller blade (D), pitch ratio (P/D) and the efficient (η) of cavitation,

Its constraint condition is:

3. the selection designing method of marine main controllable pitch propeller device according to claim 1 and 2 is characterized in that: when the check process of step C and step D all once meets the demands, then return steps A, reduce hub diameter (d _H), continue step B-D, when the check process of step C or step D does not meet the demands, adopt again among last step A-D and satisfy the size factor and the inertia key element of checking requirement, continue step e-F.

4. the selection designing method of marine main controllable pitch propeller device according to claim 1 is characterized in that: the total stress (σ among the step C on the blade _Tot) should be less than the permissible stress of blade bolt.

5. the selection designing method of marine main controllable pitch propeller device according to claim 1 is characterized in that: among the described step D, load-carrying capacity is checked to checking load-carrying capacity than (k _p), load-carrying capacity compares k _p=K _D/ K _B＞1.5,

In the formula: K _BBe blade cross section, 0.35R place load-carrying capacity, R=D/2, K _DBe the propeller hub load-carrying capacity;

$K_B=\frac{W_{0.35}\×{\mathrm{\σ}}_S\×{10}^{-3}}{R_L-R_B}$

W _0.35Be the composite bending modulus in blade cross section, 0.35R place, W _0.35=0.0448 * C _0.35* (t _0.35) ²/ 0.47

C _0.35Be 0.35R place blade chord length, C _0.35=1.973 * EAR * D/z

t _0.35Be 0.35R place blade thickness, t _0.35=(0.0433-0.00325 * z) * D

Z is a number of blade

σ _sYield point for the blade material

R _L＝0.9R

R _B＝0.35R

$K_D=\frac{k\×{d_H}^3}{{10}^2\×(R_L-L_2)}$

K is a coefficient,

d _HBe hub diameter

L ₂Be the distance of propeller shank end face of flange to propeller center.

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