Further model tests on four-bladed controllable pitch propellers

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PAPERS

OF

SHIP RESEARCH INSTITUTE

Further Model lests on Four-Bladed Controllable-Pitch Propellers

By

Atsuo YAZAKI and Nobuo SUGAI

August 1966

Ship Research Institute

Tokyo, Japan

(2)

Further Model Tests on Four-Bladed

Controllable-Pitch Propellers

By

Atsuo YAZAKI and Nobuo SUGAI

Summary

This paper presents the results of the tank tests of a systematic series of

Modified AU-type four-bladed controllable-pitch propeller models, the

expanded-area ratio of which is 0.70.

The design and calculation diagrams of the series

are given.

The same type of controllable-pitch propeller model with expanded-area

ratio of 0.55 and with non-uniform radial pitch distribution is also tested.

Introduction

One of the authors reported the results of the tank tests on the

four-bladed controllable-pitch propellers with the expanded-area ratio of

0.40 and 0.55 in the Papers of Ship Research Institute.1

Further to the work, the authors conducted a systematic testing

work with the same type of controllable-pitch propeller models with

expanded area ratio of 0.70 in the Mejiro No. 2 Experiment Tank. The

propeller model, with expanded area ratio of 0.55 and non-uniform radial

pitch distribution was also tested.

In this paper, the authors present the results of the open water

tests and some design diagrams.

Model Propellers and Open Water Tests

Model propellers used here are made of alminium alloy and they

have the diameter of 0.25 m.

Their principal particulars are given in

Table 1.

As are shown in Table 1. they have two groups of the area ratio

0.70 and 0.55.

The radial pitch distribution of the wide blade area

group is uniform, but that of the narrow blade area group is non-uniform.

The authors call the former AU-CP 4-70 and the latter AU-CP 4-55

(non-uniform).

Model propellers shown in

Fig. i are built up with four blades

and a hub to change the setting angle of the blades.

The blades are

(3)

2 aft sides of the hub.

Therefore, it is possible to adjust the blades to a

given setting position by rotating the blades to the ahead

or astern

direction and fixing them by the set-screws.

Open water tests were carried out in the No. 2 Experiment Tank

according to the ordinary practice.

To obtain the net thrust, the correction for the resistance of the

screw hub was made at various speed of advance for the measured

thrust.

The Reynolds number Rn of the tests is shown in Table 1.

The tests were conducted at various angular blades settings, that

is, the blades were rotated by 5 degree intervals to increase or decrease

the pitch.

Tests Results

The results of the tests for each propeller are shown in Figs. 2 to

5 in the form of J-K7, KQ,

O

diagrams.

In these figures, 0 denotes the adjusted angle of the blades from

the initial setting, therefore "0=0° " means the initial setting

condi-tion of the blades of each propeller.

Positive sign of the advance constant J and the thrust coefficient

K7 corresponds to the propeller in ahead running and negative sign to

the propeller in astern running.

Negative value of the torque coefficient

KQ shows that the propeller is rotated by the current.

When the effective pitch

is adjusted to nearly zero, curves of KQ

show the singular characteristics.

And, in curves of K7. remarkable

discontinuity comes out at a certain fixed speed.

Under this speed of

advance, the waves induced are in front of the propeller, but when

speed of advance becomes higher than this speed, the waves are left

behind the propeller, so remarkable discontinuity in curves of K7 will

be found at this particular speed.

Values of K7, K( and i read from these figures are tabulated in

Tables 2 to 5.

Design Diagrams

Fig. 6 shows the B-ô type design diagram for the propeller with

the expanded area ratio of 0.70, AU-CP 4-70.

The metric units are

used, and the density of sea water is assumed as 104.51 kg sec2/m4.

It is possible to determine such a principal dimensions as diameter

and pitch ratio of the four-bladed controllable-pitch propellers, applying

this diagram and similar diagrams for AU-CP 4-40 and ATJ-CP 4-55 at

the initial stage of design.

(4)

3 Another types of diagrams which are convenient for calculating the

performances of the propellers when their blades setting angles are

adjusted are shown in Figs. 7 to lo.

Symbols in these figures are as follows;

T; thrust in metric tons, P; delivered horse power in PS.

D; diameter in meter, V; speed of advance in knots.

Nc; N/lOU and N is number of revolutions of the propeller per

minute.

Effect of Pitch Distribution

Fig. 11 shows the radial pitch distribution of M.P. No. 1575.

Comparing Figs. 5 and 10 with Figs. 1.6 and 1.14 in the previous

paper' we find the effect of the pitch distribution on the performance

for the controllable-pitch propeller.

Acknowledgements

The authors wish to acknowledge the valuable co-operation and

as-sistance of the late Mr. Einosuke Kuramochi and the staff of our Institute

who assisted to carry out the experiments and the calculations.

We also

wish to acknowledge the Yokohama Ship Yard, Mitsubishi Heavy Industry

Co. Ltd., as most of the work reported here were carried out under

the co-operative research project with that Company.

Reference

(1) A Yazaki, Model tests on four-bladed controllable-pitch propellers. Papers of Ship

(5)

4 Table 1.

Principal Particulars of Model Propellers

Model Propeller No.

1572

1573

1574

1575

Diameter (m), D

0.250 _0.250

Boss Ratio, d/D

_0.30

Pitch [Initial) (m), H

0.250

0.200

0.150

0.200 Pitch Ratio [Initial),

HID

1.00

0.80

0.60

0.80 Exp. Area Ratio, AE

_0.70

_0.55

Blade Thickness Ratio,

t0/D

_0.050

Mean Blade Width Ratio,

BID

0.392

0.308 Max. Blade Width Ratio,

_Bm,ID

0.464

0.364 Form of Blade Section

Aerofoil (MAU)

MAU

NunTher of Blades, Z

4

4 Angle of Rake

_o

_O

Revolution (r.p.$) at tests, n

12.0

12.0 Temp. of Water (°C), r

_{8.0 22.0}

_8.2-17.0

Reynolds Number, R=nD2/

_{5.44x105.-7.85x105}

5.47>< 10

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46 CORRESPOND

50 FIGURES IN BRACKTS

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FigS. M. P. No. 1575

13

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Type

AUCP470

2

3

4

5

6

8

9 lo

2

3 Fig. 6.

/B9 ö.Diagram (AU-CP 4-70)

(16)

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0.0

0.0 bQ°

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N

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V/ND

Fig. 7.

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H/D_-1.00)

15 T:Thrust (KT)

\

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.

:

AU-CP4-70

D:

oIe'r

l

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(17)

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Calculation Diagram (AU-CF

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o

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e

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Fig. 9.

Calculation Diagram (AU-CP 4-70, H/D=0.60)

Ut

0 7 0

17

2

(19)

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Fig. 10.

Calculation Diagram (AU-CP 4-55 (non.uniform) H/D=O.80)

0.12

0.10

0.08

0.06

0.04 .

0.02 o

-0.02

-0.04

(20)