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Turbomachinery
Hasan OzcanAssistant Professor
Mechanical Engineering DepartmentFaculty of Engineering Karabuk University
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Introduction
Hasan Ozcan, Ph.D, (Assistant Professor)
B.Sc :Erciyes University, 2009M.Sc :Karabuk University, 2011Doctorate :University of Ontario Institute of
Technology, 2015
Research Fields: Thermal system design, renewable energy, hydrogen production, Energy Storage
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IntroductionMarking SchemeMidterm – 40%Project – 20% (added to final exam ‐ elective)Final Exam – 60%
SourcesBasic Concepts in Turbomachinery ( Ingram, 2009)Turbomachinery Performance Analysis (Levis, 1996 )Fluid Mechanics and thermodynamics of Turbomachinery (Dixon and Hall, 2010)
Course ContentWeek 1: Introduction and Basic PrinciplesWeek 2: Relative and Absolute MotionWeek 3: Turbomachine OperationWeek 4: Basic Concepts for Fluid MotionWeek 5: Dimensionless Parameters in TurbomacineryWeek 6: Efficiency and Reaction for TurbomachineryWeek 7‐9: Axial flow MachinesWeek 9‐12: Hydraulic Turbines Week 11‐13: Analysis of Pumps Week 14: Project presentations
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Introduction to Turbomachinery
What is a turbomachine?
‐ Turbomachine is a device exchanging energy with a fluid by either absorbing
from or extracting energy to the fluid.
‐ The energy extracting devices are called Turbine, while energy absorbing devices
can be called pump, blower, fan, and compressor.
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Introduction to Turbomachinery
Some Applications of Turbomachinery
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Introduction to Turbomachinery
Classification of Turbomachines
‐ Energy Extracting – Energy Absorbing
‐ Flow Direction: Axial, radial, mixed
‐ Fluid type: Compressible, incompressible
‐ Impulse, reaction (For hydro turbines)
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Introduction to Turbomachinery
Energy Extracting Devices
Gas Turbine: Energy production is accomplished by extracting energy from a
compressible gas such as air, helium, or CO2.
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Introduction to Turbomachinery
Energy Extracting Devices
Steam Turbine: Energy production is accomplished by extracting energy from
superheated high pressure steam. Many other liquid woring fluids are also in use.
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Introduction to Turbomachinery
Energy Extracting Devices
Wind Turbine: Converts kinetic energy of air into mechanical energy.
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Introduction to Turbomachinery
Energy Extracting Devices
Hydro Turbine: Hydoturbines are used to convert the potential energy of water
into mechanical energy.
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Introduction to Turbomachinery
Energy Absorbing Devices
Pumps: Absorbs energy to increase the pressure of a liquid.
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Introduction to Turbomachinery
Energy Absorbing Devices
Fans: Low pressure increase of high flow rate gases.
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Introduction to Turbomachinery
Energy Absorbing Devices
Blowers: Medium pressure increase of medium flow rate gases.
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Introduction to Turbomachinery
Energy Absorbing Devices
Compressors: High pressure increase of low flow rate gases
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Introduction to Turbomachinery
Positive displacement vs dynamic turbomachines
Courtesy of slidesharecdn.com
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Introduction to TurbomachineryFluid Type
Compressible: (Fans, blowers, compressors, gas turbines)
Incompressible: (hydro turbines)
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Introduction to Turbomachinery1. Coordinate SystemSince there are stationary and rotating blades in turbomachines, they tend to form a cylindrical form,
represented in three directions;
1. Axial
2. Radial
3. Tangential (Circumferential ‐ rθ)
Axial View
Side View
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Introduction to Turbomachinery1. Coordinate SystemThe Velocity at the meridional direction is:
Where x and r stand for axial and radial.
NOTE: In purely axial flow machines Cr = 0, and in purely radial flow machines Cx=0
Axial ViewAxial View Stream surface View
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Introduction to Turbomachinery1. Coordinate SystemTotal flow velocity is calculated based on below view as
Stream surface View
The swirl (tangential) angle is (i)
Relative Velocities
Relative Velocity (ii)
Relative Flow Angle (iii)
Combining i, ii, and iii ;
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.1. Continuity Equation (Conservation of mass principle)
2.2. Conservation of Energy (1st law of thermodynamics)
Stagnation enthalpy;
if gz = 0;
For work producing machines
For work consuming machines
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.3. Conservation of Momentum (Newtons Second Law of Motion)
• For a steady flow process;
• Here, pA is the pressure contribution, where it is cancelled when there is rotational symmetry. Using
this basic rule one can determine the angular momentum as
• The Euler work equation is:
where
The Euler Pump equation
The Euler Turbine equation
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
Writing the Euler Eqution in the energy equation for
an adiabatic turbine or pump system (Q=0)
NOTE: Frictional losses are not included in the Euler Equation.
2.4. Rothalpy
An important property for fluid flow in rotating systems is called rothalpy (I)
and
Writing the velocity (c) , in terms of relative velocities :
, simplifying;
Defining a new RELATIVE stagnation enthalpy;
Redefining the Rothalpy:
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Introduction to Turbomachinery2. Fundamental Laws used in Turbomachinery
2.6. Second Law of Thermodynamics
The Clasius Inequality :
For a reversible cyclic process:
Entropy change of a state is , , that we can evaluate the isentropic process when the process is
reversible and adiabatic (hence isentropic).
Here we can re‐write the above definition as and using the first law of thermodynamics:
dQ‐dW=dh=du+pdv and
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Introduction to Turbomachinery
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Introduction to Turbomachinery2. Fundamental Laws used in Turbomachinery
2.5. Bernoulli’s Equation
Writing an energy balance for a flow, where there is no
heat transfer or power production/consumption, one obtains :
Applying for a differential control volume:
(where enthalpy is
When the process is isentropic ), one obtains
Euler’s motion equation:
Integrating this equation into stream
direction, Bernoulli equation is obtained:
When the flow is incompressible, density does not change, thus the equation becomes:
where and po is called as stagnation pressure.
For hydraulic turbomachines head is defined as H= thus the equation takes the form.
NOTE: If the pressure and density change is negligibly small, than the stagnation pressures at inlet and outlet
conditions are equal to each other (This is applied to compressible isentropic processes)
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2017 Midterm Q: Using the first law of thermodynamics, show the Bernoulli equationyields to Hin = Hout for hydraulic turbomachines
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.7. Compressible flow relations
For a perfect gas, the Mach # can be written as, . Here a is the speed of sound, R, T and are
universal gas constant, temperature in (K), and specific heat ratio , respectively.
Above 0.3 Mach #, the flow is taken as compressible, therefore fluid density is no more constant.
With the stagnation enthalpy definition, for a compressible fluid: (i)
Knowing that:
and , one gets 1 (ii)
Replacing (ii) into (i) one obtains relation between static and stagnation temperatures: (iii)
Applying the isentropic process enthalpy ( / ) to the ideal gas law ( ): / and one
gets: (iv)
Integrating one obtains the relation between static and
stagnation pressures : (v)
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Introduction to Turbomachinery2. Fundemental Laws used in TurbomachineryDeriving Speed of sound
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
Deriving Speed of sound
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
Deriving Speed of sound
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Introduction to Turbomachinery
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2. Fundemental Laws used in Turbomachinery
2.7. Compressible flow relations
Above combinations yield to many definitions used in turbomachinery for compressible flow. Some are listed
below:
1. Stagnation temperature – pressure relation between two arbitrary points:
2. Capacity (non‐dimensional flow rate) :
3. Relative stagnation properties and Mach #:
HOMEWORK: Derive the non dimensional flow rate (Capacity) equation using equations (iii), (v) from the previous
slide and the continuity equation
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Introduction to Turbomachinery2. Fundamental Laws used in Turbomachinery
2.7. Compressible flow relations
Relation of static‐relative‐stagnation
temperatures on a T‐s diagram
Temperature (K)
Temperature – gas properties relation
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.8. Efficiency definitions used in Turbomachinery
1. Overall efficiency
2. Isentropic – hydraulic efficiency:
3. Mechanical efficiency:
2.8.1 Steam and Gas Turbines
1. The adiabatic total‐to‐total efficiency is :
When inlet‐exit velocity changes are small: :
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.8.1 Steam and Gas Turbines
Temperature (K)
Enthalpy – entropy relation for turbines and compressors
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2. Total‐to‐static efficiency:
Note: This efficiency definition is used when the kinetic energy is not utilized and entirely wasted. Here, exit
condition corresponds to ideal‐ static exit conditions are utilized (h2s)
2.8.2. Hydraulic turbines
1. Turbine hydraulic efficiency
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.8.3. Pumps and compressors
1. Isentropic (hydraulic for pumps) efficiency
2. Overall efficiency
3. Total‐to‐total efficiency
4. For incompressible flow :
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.8.4. Small Stage (Polytropic Efficiency) for an ideal gas For energy absorbing devices
integrating
For and ideal compression process , so
Therefore, the compressor efficiency is:
NOTE: Polytropic efficiency is defined to show the differential pressure effect on the overall efficiency, resulting in an
efficiency value higher than the isentropic efficiency.
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Introduction to Turbomachinery2. Fundemental Laws used in Turbomachinery
2.8.5. Small Stage (Polytropic Efficiency) for an ideal gas For energy extracting devices