Ship Power Systems and Design Part 3

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Ship Power

Ship Power

Systems and

Systems and

Design

Design

Course no.: 21 444/924

Hossein Ghaemi

Sem. I, 2009/2010

University of Stratchclyde, Faculty of Engineering

Department of Naval Architecture and Marine Engineering

Part 3

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

2

PART 3

PART 3

Gas Turbine Propulsion

Gas Turbine Propulsion

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

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Introduction to Part 3

This part of the lecture is devoted to

introduction to gas
turbine as a (part of) prime mover in ship
propulsion
system.

It delivers basic information on different gas

turbine
elements, thermodynamics of different cycles
and
configurations, giving some examples of
application of
gas turbine in marine technology.

The aim is building a general idea about

operation and
features of gas turbine propulsion.

The aspects of design and construction of gas

turbines
are not included in.

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Gas Turbine as a Marine Prime Mover

Gas turbine uses fuel energy to produce

mechanical output

power

, either as

torque

through a rotating shaft (industrial

and marine gas turbines) or as jet power in the form of

thrust/velocity

through an exhaust nozzle (aircraft jet

engines).
The

fuel energy

is added to the

working substance

, which is

gaseous in form and most often air, either by direct internal
combustion or indirectly through a heat exchanger. The
heated working substance, air co-mixed with combustion
products in the usual case of

internal combustion

, acts on a

continuously rotating turbine to produce

power

.

The gas turbine is thus

distinguished from heat engine

types

where the working substance produces mechanical power by
acting intermittently on an enclosed piston, and from steam
turbine engines where the working substance is water in
liquid and vapor form.

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GE Marine Engines’ LM2500 aero-derived gas turbine showing

(from left to right) the compressor(1), combustor (or burner) (2),

high pressure turbine (3) and low pressure power turbine (4).

Gas Turbine – General View

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Gas Turbine – Main Elements

Compress
or inlet

Front
compressor

Compressor
intermediate

Main
accessory
gearbox

Rear
compresso
r

Diffus
er

Combustion
section

Turbine
nozzle

Rear
compressor
drive turbine

Front
compressor
drive turbine

Exhaust
case

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h

tt

p

:/

/w

w

w

.h

o

w

st

u

ff

w

o

rk

s.

co

m

/t

u

rb

in

e

3

.h

tm

Principles

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Marine Gas Turbine

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Gas Turbine Power
Plant

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Gas Turbine for Jet
Propulsion

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Model of ideal gas:

The ideal gas can be regarded as a system of

tiny, rigid, randomly distributed particles which undergo chaotic
motion. The distances between them are much larger than their
dimensions and they exert no adhesive forces on one another. The
particles have dierent speeds, they collide with the walls of the vessel
and with each other in such a way that they change their energy and
momentum.

Temperature

represents the thermal level of the fluid and

(according to statistical mechanics of gases) it may be defined as a
measure of the kinetic energy of translatory motion of gas particles.
The lowercase letter t denotes temperature measured in the
Centigrade (Celsius) scale, while the capital letter T – temperature in
the absolute (Kelvin) scale.

Definitions

Internal energy

may be understood as the sum of the kinetic energy

of all kinds of motion of a gas (translatory, rotational and vibrational),
plus the potential energy resulting from the relative mutual location of
gas molecules, plus the chemical energy of the gas (the energy used
to create the compound). The internal energy of a unitary mass of gas
is denoted by the lowercase letter u. The physical unit of u is J/kg or
kJ/kg .

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Pressure

is understood as the force per unit of area exerted by the

fluid on any surface, either on the boundary of the vessel or immersed
in the fluid. Pressure always acts perpendicularly to the surface. The
lowercase letter p is used to denote pressure and its value is
expressed in Pascals, Pa = N/m2 . In practice multiple units are used,
i.e. 1 kPa = 103 Pa, and 1 MPa = 106 Pa.

Density

denoted by the Greek letter

, describes the concentration of

matter M in volume V:

 =M/V. The unit of gas density  is kg/m

3

.

Specific volume

denoted by the lowercase letter v, is inverse in value

to the density of the gas v =V/M=1/

. The unit of specific volume v is

m

3

/kg.

Viscosity

is understood as molecular cohesion and interaction

between adjacent layers of fluid. The coecient of dynamic viscosity

 is

expressed in kg/m·s or in poises, 1 P = 0.1 kg/m·s . The coefficient of
kinematic viscosity

= is expressed in m

2

/s or in stokes, 1 St = 10

-

4

m

2

/s.

State equation:

The relation between temperature T, pressure p and

specific volume v is called the state equation: pv=RT. The gas constant
R is given by the relation R=R

m

/M

m

, where R

m

stands for the universal

gas constant, R

m

= 8314 J/kg·K, while M

m

is the molecular mass of the

gas.

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Enthalpy

h of a unit mass of gas may be defined by the following

relation

h = u + p · v

The product p·v is interpreted as the work necessary to pump the
medium into the considered region, or to the exit from it. The specific
enthalpy h is expressed in

J/kg

or kJ/kg.

Kinetic energy

E of fluid mass M is calculated as follows

where w stands for the velocity of the gravity centre of mass M.

Specific kinetic energy

of a unitary mass is written in the form of

and is measured in J/kg.

2

2

Mw

E

2

2

w

M

E

e

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Heat

is understood as a form of energy transmission and expressed in J

(or kJ), while the unit of specific heat q is a J/kg. The total heat q

t

related

to a thermodynamical process is the sum of the nett heat q from
external sources and the heat q

f

due to friction present in the actual

process.

Specific heat at constant pressure

c

p

is the quantity of heat

required to raise the temperature of one kilogramme of a substance by
one Kelvin (or one degree Centigrade) at constant pressure, (

J/kg.K

).

Specific heat at constant volume

c

v

is the quantity of heat required

to raise the temperature of one kilogramme of a substance by one
Kelvin (or one degree Centigrade) at constant volume, (

J/kg.K

)

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R

c

c

v

p

R

c

R

c

v

p

1

1

1

v

p

c

c

For ideal gases the heats c

p

and c

v

are constant values, but for actual

gases
they depend on the temperature and pressure.

For a semiperfect gas:

)

(

)

(

T

c

c

T

c

c

v

v

p

p

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In practical applications average values of specific heats in a given
range of temperatures (from T

1

to T

2

) are used:

Also

Specific entropy:

The increase of specific entropy s can be

calculated as the ratio of total added heat to temperature

dT

dq

ds

t

J/(kg.K)

1

2

0

0

1

2

0

0

1

2

1

2

T

T

c

c

c

T

T

c

c

c

T

v

T

v

v

T

p

T

p

p

or

2

1

2

1

2

1

2

1

)

(

1

)

(

1

1

2

1

2

T

T

v

T
T

v

T

T

p

T

T

p

dT

T

c

T

T

c

dT

T

c

T

T

c

dT

c

du

dT

c

dh

v

p

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Specific technical work

dl for a unit mass M of gas can be given in

the form

dp

v

dl

J/kg

Polytropic process:

The polytropic process is given by the following

relation

.

cons

v

p

n

n: polytropic
exponent





n

n

p

p

T

R

n

n

l

1

1

2

1

2

1

1

1

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Adiabatic Process:

An adiabatic process is defined as a process without

any heat supplied to the medium from external reservoirs

0

2

1

q

Reversible adiabatic process:

If additionally the heat supplied to the

medium due to friction is equal to zero it is so-called reversible
adiabatic process. For a reversible adiabatic process:

0

ds

(isentropic process)

.

cons

v

p





1

1

2

1

2

1

2

1

1

1

p

p

T

R

h

h

l

s

s

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External technical work

is defined by the relation

friction losses

2

1

2

1

2

1

2

1

h

h

q

l

l

f

e

2

1

2

1

e

s

l

l

Turbine internal efficiency

is defined as

s

s

e

i

h

h

h

h

l

l

2

1

2

1

2

1

2

1

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T-s Diagram -1

Elementary change of
total heat supplied to the
medium

isothermal

process

isochoric

process

isobaric

process

isentropic

process

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Constant pressure process

Constant volume process

T-s Diagram -2

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T-s Diagram -3

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h-s Diagram

For

perfect gases

the specific heat at constant

pressure

c

p

is a constant

value and the

enthalpy of

gas depends linearly on temperature

.

Thus it is enough to

multiply the temperature scale T

by the value of c

p

in the T-s diagram to obtain an h-s

diagram.

Then, the lines of particular thermodynamical

processes may look

identical in T-s and h-s

diagrams.

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Thermodynamic cycle:

A sequence of consecutive thermodynamical

processes is known as a thermodynamical cycle (closed cycle) if the
parameters of the medium at the beginning are exactly the same as the
parameters in the end state.

Thermodynamic cycle of a heat engine

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Thermal cycle efficiency

Thermal efficiency:

The ratio of net output energy to fuel input energy

for the cycle.

Total efficiency of ship turbine propulsion system

engine

B

propeller

E

total

P

P

engine

f

engine

B

W

m

P

 

f

n

tT

m

W

E

1

2

1

2

1

1

1

q

q

q

q

q

q

l

t

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Assumptions made for an ideal gas turbine (theoretical)
cycle

Processes are reversible, isobaric and adiabatic;

Ideal gas with constant specific heat c

p

and c

v

and constant adiabatic exponent;

Constant flow, no flow losses;

No pressure or mechanical losses;

Ideal thermal efficiency.

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1

2

1

2

1

1

1

q

q

q

q

q

q

l

cycle

cycle





3

2

3

2

3

2

3

1

1

T

T

T

c

T

T

c

h

h

q

p

p





4

1

4

1

4

1

4

2

1

T

T

T

c

T

T

c

h

h

q

p

p

1

1

2

1

2





p

p

T

T

1

1

2

4

3





p

p

T

T

4

1

3

2

4

3

1

2

T

T

T

T

T

T

T

T

 





1

1

1

1

1

2

p

p

cycle

q

1

q

2

Brayton cycle

3

4

1

T

T

cycle

The ideal version of the
gas turbine cycle is
known as the Brayton
cycle.

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cycle

 

1

1

cycle

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Real Brayton Cycle (open cycle)

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The medium

dT

T

c

c

T

T

p

T

T

p

)

(

0

0

| 

dt

t

c

t

t

c

t

t

p

t

t

p

)

(

1

2

1

2

1

2

1

|

a

f

m

m

068

.

0

ST

)

023

.

0

016

.

0

(

6

3

GT

ST

Combustion

temperature:

1800-2000C

(for

TG~1450C) =3÷6

dT

T

c

h

T

T

p

)

(

2

1

T

c

h

T

T

p

|

2

1

T

c

h

p

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Combustion

Min. required oxygen

ST

O

kg

kmol

o

s

h

c

32

32

4

12

min

2

2

O

of

kg

32

O

of

kmol

1

Calorific value of gas fuel





3

n

m

2

2

4

2

6

2

4

2

H

C

77060

H

C

55620

H

C

59790

H

C

62680

CH

35700

H

10650

CO

12450

nm

kJ

W

CO

-

carbon

oxide

2

H - hydrogen

4

CH

-
methan
e

6

2

H

C

-
ethan
e

-
ethylen
e

4

2

H

C

2

2

H

C

-
acethylen
e

n

m

H

C

Other
hydrocarbons

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C

C

p

p

T

T

s

 1

1

2

1

2





1

2

1

2

1

2

1

2

T

T

T

T

h

h

h

h

s

s

C

1

2

1

2

T

T

c

h

h

l

C

p

C

1

2

1

2

1

2

1

2

1

2

1

2

1

T

T

T

T

T

T

T

T

h

h

h

h

s

C

s

s

C





1

1

1

1

2

1

1

2

T

T

T

c

T

T

c

l

s

C

p

C

s

C

p

C

C





1

1

1

1

2

1

C

C

p

p

T

c

l

C

p

C

C





1

2

p

p

C

1

2

p

p

p

C

Elements – 1: Compressor

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Elements – 1: Compressor

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Elements – 1: Compressor

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Elements – 1: Compressor

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Elements – 1: Compressor

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Elements – 1: Compressor

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Elements – 1: Compressor

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3

2

2

2

)

(

h

m

m

W

m

h

m

f

B

f

Burner

2

3

h

2

h

3

m

2

m

3

m

f

h

f

.m

f

W.m

f

h

f

.m

f

<<W.m

f

η

B

Ignore it!

3

2

3

2

h

W

h

h

m

m

B

f

3

2

3

T

c

W

T

c

T

c

B

p

B

C

p

B

p

Elements – 2: Burner (Combustor)

B

f

f

h

m

h

m

m

W

m

Q

2

2

3

2

1

)

(

Or
:

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Elements – 2: Burner (Combustor)

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Elements – 2: Burner (Combustor)

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Elements – 2: Burner (Combustor)

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Elements – 2: Burner (Combustor)

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T

T

p

p

T

T

s

 1

3

4

3

4





s

s

T

T

T

T

T

h

h

h

h

4

3

4

3

4

3

4

3

4

3

4

3

T

T

c

h

h

l

T

p

T

s

T

s

s

T

T

T

T

T

T

T

T

T

h

h

h

h

4

3

4

3

4

3

4

3

4

3

4

3





3

4

3

4

3

1

T

T

T

c

T

T

c

l

s

T

p

T

s

T

p

T

T





T

T

p

p

T

c

l

T

p

T

T

1

3

4

3

1





4

3

p

p

T





T

T

T

T

p

T

T

T

c

l

1

3

1

1

Elements – 3: Turbine

p

3

p

4

4

3

4s

h

s

expansi
on

3

4

4

P

B

3

Turbin
e

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Elements – 3: Turbine

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Elements – 3: Turbine

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C

T

m

B

l

m

l

m

P

2

3

W

m

P

Q

P

f

B

B

engine

1













1

1

1

1

1

1

1

1

1

2

1

3

2

3

1

1

2

2

3

1

3

4

1

3

2

2

3

3

1

2

2

2

3

3

2

2

3

3

2

3

C

C

C

C

T

T

p

p

c

T

T

c

m

m

p

p

c

m

m

p

p

T

T

c

h

m

h

m

h

h

m

h

h

m

h

m

h

m

l

m

l

m

C

p

C

B

p

C

p

C

T

p

T

m

B

B

m

B

C

T

m

engine

 

 













1

1

1

1

1

1

1

1

3

2

3

1

2

3

1

1

3

C

C

C

C

T

T

C

C

p

C

B

p

C

C

p

C

T

T

p

T

m

B

engine

c

T

T

c

m

m

c

m

m

T

T

c

Gas Turbine Set as a Prime Mover (Engine)

B

h

m

h

m

Q

1

2

2

3

3

1

(derived for burner)

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- pressure losses
coeff.





1

3

2

3

,

,

,

,

,

,

,

,

,

,

,

,

T

T

m

m

c

c

c

f

T

C

B

p

T

p

C

p

m

B

C

T

engine

2

3

,

,

,

,

,

m

m

c

c

c

T

C

B

p

T

p

C

p

Mainly depend on temperature and pressure

,

,

,

,

m

B

C

T

Individual characteristic parameters, depending
on the system elements and their constructions

1

C

C

C

T

(T

1

: ambient temp.)

3

1

3

,

,

T

f

T

T

f

engine





Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

49

Gas Turbine Set as a Prime Mover (Engine)

engine

engine

=

GT

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

50

Choice of

and T

3

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

51

Polytropic efficiency

n

n

p

1

1

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

52

Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

53

Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

54

Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

55

Gas Turbine Set as a Prime Mover (Engine)

Problem with space and weight?

Install gas

turbine!

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

56

Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

57

Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

58

Two-shaft (double shaft) Gas Turbine Set as a Prime Mover
(Engine)

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Ship Power Systems and Design

59

Two-shaft (double shaft) Gas Turbine Set as a Prime Mover
(Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

60

Two-shaft (double shaft) Gas Turbine Set as a Prime Mover
(Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

61

Three-shaft Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

62

Three-shaft Gas Turbine Set as a Prime Mover (Engine)

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

63

Gas Turbine Propulsion – example1

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Ship Power Systems and Design

64

Gas Turbine Propulsion – example2

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65

Gas Turbine Propulsion – example3

An example of the gas turbine arrangement of a destroyer

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66

Gas Turbine Propulsion – example4

Gas turbine

arrangement

(for a destroyer)

a) With electrical

generators driven by
diesel engines

b) With electrical

generators driven by
gas turbines

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67

2

4

2

2

*

T

T

T

T

R

max

T

T

real

R

Order of
regeneration:

)

85

.

0

75

.

0

(

R

9

.

0

R

For closed

cycles

The Idea: Heating up the inlet air
to the combuster to increase the
thermal efficiency

Regenerative open cycle

2

4

.

3

.

.

*

2

T

T

T

T

c

m

Q

q

regen

p

comb

comb

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Ship Power Systems and Design

68

Regenerative open cycle

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Ship Power Systems and Design

69

Regenerative open cycle

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Intercooling

The Idea: Cooling down the inlet air to the compressor,
which consequently gives higher total efficiency

2

1



1

2

2

1

1

opt

cool

C

C

C

C

p

C

T

c

l



1

2

2

1

opt

cool

C

C

C

C

l

l

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Ship Power Systems and Design

71

Intercooling





2

1

1

1

1

1

1

1

1

1

1

1

1

1

1

2

1

cool

C

C

C

C

C

C

C

C

C

C

C

C

C

C

p

C

p

C

p

C

C

C

T

c

T

c

T

c

l

l

l

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Reheating (Sequential combustion)

The idea: to approach isothermal expansion to increase turbine power.

2

1

T

T

T

2

1

rh

T

T

T

l

l

l

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Ship Power Systems and Design

73













T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

p

T

T

p

T

T

p

T

T

T

T

T

c

T

c

T

c

l

l

l

1

1

1

1

1

3

1

2

3

1

1

3

2

1

2

1

1

1

1

rh

Reheating (Sequential combustion)

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Ship Power Systems and Design

74

More burners?

2%-4% increase in efficieny!

Reheating (Sequential combustion)

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75

Regeneration + Intercooling +
Reheating

Regeneration + Intercooling +
Reheating

Regeneration + Intercooling +
Reheating

Regeneration + Intercooling +
Reheating

Ericsson Cycle

Regeneration + Intercooling +
Reheating

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76

Ericsson Cycle

1

2

1

2

4

3

3

1

ln

ln

p

p

T

R

l

q

p

p

T

R

l

q

C

T

4

3

3

1

2

1

4

3

3

ln

ln

ln

p

p

T

R

p

p

T

R

p

p

T

R

E

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77

Comparison of different cycles

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78

Gas turbine chacteristic parameters in

brief

 

d

f

GT

e

eGT

W

m

P

1

-

Effective

efficiency

kg

kJ

2

m

P

l

eGT

GT

e

2 – Effective work





kWh

kg

2

eGT

e

P

m

d

3 – Spec. air required





kWh

kg

eGT

f

e

P

m

b





kWh

kg

3600

eGT

e

l

d





kWh

kg

3600

W

b

eGT

e

5 – Compress.
efficiency

)

30

20

( 

e

d

)

4

.

0

2

.

0

(

e

b

%)

92

%

40

(

T

%)

90

%

80

(

C

%

99

%

97 

m

6 – Turbine
efficiency

7 – Mech. efficiency

4 – Spec. fuel
consump.

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79

Manufacturer

RR

GE

Type

Allison

601

KF9

Allison

601

KF11

Spey

SM1C

WR21

LM500

LM1600

LM2500

LM2500

+

Brake power, kW

6500

7800

19500

25240

4400

14900

24000

26000

Output speed, rpm

5500

3600

7000

7000

3600

3600

Specific fuel
consumption, g/kWh

250

250

230

200

266

233

238

236

Air mass flow, kg/s

66

72

16.3

47

68

78

Specific power, kJ/kg

295

350

270

317

353

334

Specific air
consumption, kg/kWh

12.2

10.3

13.3

11.4

10.2

10.8

Weight, kg

25700

46000

15440

22000

Specific mass, kg/kW

1.4

1.8

1.04

0.92

Length, m

~5

~5

7.5

8.0

6.5

8.3

Width, m

~1.9

~1.9

2.3

2.7

2.3

2.7

Height, m

~2.5

~2.5

3.1

4.8

3

3

Volume, m

3

~29

~29

53.1

103.6

44.9

67.2

Specific volume,
dm

3

/kW

~4.5

~4.5

2.7

4.1

2.5

2.8

Rolls-Royce and General Electric gas turbines for marine

applications

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80

Other
examples

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81

1947 – UK: GATRIC Metropolitan Vickers, 1870 kW, 12.8%,

(torpedo)

1951: British Thomson (regenerated), 880 kW, 20.1%, (Auris,

tanker)

60’s: Ro-Ro, Ferries, LNG, Hovercrafts, HSC

Most installed:

General Electric LM2500, LM100, LM300, LM1500, FT4,

Gnome,

Rolls-Royce Allison 601 KF11, Spey SM1C, WR21

Olympus, Russian GTU M2, GTU M3, GTKI, GTG-1

1000 naval ships are equipped with more than 2500 gas

turbines

Gas turbine, history and
today

The history goes on …

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82

Zubr - Hovercraft

example

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

83

Aquastrada – high speed yacht

example

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Ship Power Systems and Design

84

Passenger – car ferry

example

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Part 3: Gas Turbine Propulsion

Ship Power Systems and Design

85

Transatlantic high speed ship

example

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Ship Power Systems and Design

86

Invincible – British airplane carrier

example

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Ship Power Systems and Design

87

Bora – Russian corvette

example

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88

Asagiri – Japanese destructor ship

example

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89

Perry – American fregat

example


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