Faculty of Engineering & Technology, SRM University, Kattankulathur - 603203 School of Mechanical Engineering

Department of Mechanical Engineering

COURSE PLAN

COURSE CODE: ME0302 COURSE TITLE: GAS DYNAMICS AND TURBO MACHINERY SEMESTER: VI ACADEMIC YEAR: 20l3-l4/EVEN Sem (Dec 2013 - Apr 2014) ..

SECTION DETAILS Sec tio n

A

B

C

CLASS ROOM No.

MEA 301

MEA 302

MEA 303

DETAITS OF FACULTY MEMBERS

NAME ROOM Inter No. com

No.. Mr. P.Chandrasekaran MEHI021 1824

B Mr. P.Sudhakar MEHI021 1824

A Mr. D.Premnath MEA203 1809

E-MAILID

chandrasekaran. p@ktr.srmuniv.ac.in

sudhakar.p@ktr.srmuniv.ac.in

premnath.d@ktr.srrnuniv.ac.in

STUDENT CONTAC TTIME

12.30 ­

0

E

MEA 304

MEA 401

Mr.R.Senthil

Mr.A.Perungosh

MEEI021 A MEBI01

1834

1832

senthi l.r@ktr.srmuniv.ac.in

perungosh.a@ktr.srmuniv.ac.in

1.30 pm on

Friday

F MEA 402 Mr. S.Panneerselvam MEH502 1805 panneerselvam@ktr.srmuniv.ac.in

G MEA 403 Mr. P.Sundram MEH101 - sundram.p@ktr.srmuniv.ac.in

H MEA 404 Mr. M.DeenadayaJan MEH313 - deenadhayalan.m@ktr.srmuniv.ac.in

DIRECT ASSESSMENT DETAILS

Name of Marks Topics Tentative date Duration assesment

Cycle test 1 10 Fundamentals of compressible flow & 05/02/2014 100 minutes flow through variable area ducts-nozzles and diffusers, flow with normal shock

Surprise test 5 Flow with normal shock 20102/2014 10-15 minutes Cycle test 2 10 Flow with normal shock,Fanno and 05/03/2014 100 minutes

Rayleigh flow Attendance 5 Model 20 Entire syllabus 15/04/2014 3 hours examination End semester 50 Entire syllabus 30104/2014 3 hours examination

1. EXPECTED LEARNING OUTCOMES OF THE COURSE

L T P C

GAS DYNAMICS AND TURBO MACHINERY ME0302 3 2 4 Prerequisite

Thermodynamics and Fluid Mechanics

0

Student outcomes Program Educational Objectives The main objective of the B.Tech in Mechanical Engineering Program is to provide a periodically-updated curriculum so that, following the completion of the program and with a few years of experience, our alumni will have the expertise to: I. Practice 2. Enhance 3. Solve industrial, 4. Work in large mechanical professional practice cross-functi onal engineering in to meet the global

social, and environmental teams and pursue

different disciplines standards with problems with life-long towards system ethical and social appropriate learning. design, realization. responsibility. techniques and manufacturing. tools.

(a) an ability to apply X X knowledge of mathematics, science, and engineering

(c) an ability to design a X X X system, component, or process to meet desired needs within realistic constraints such as economic, environmental, social, political, ethical, health and safety, manufacturability, and sustainability (e) an ability to identify, X X formulate, and solve engineering problems

Course designed by Department of Mechanical Engineering 1 Student outcome a Ib Ic Id Ie If Ig Ih Ii I i Ik

x I Ix I Ix I I I I I I PROFESSIONALGENERAL BASIC ENGINEERlNG SCIENCES2 Category SUBJECTS (P)

ES (B) (G) SCIENC AND TECHNICAL ART (E)

X

Broad area Design Thermal Genaral (for professional courses only, i.e

3

X'under P' category)

4 Course Mr.P.Sudhakar Coordinator I

2.MAPPING BETWEEN INSTRUCTIONAL OBJECTIVES AND STUDENT OUTCOMES

INSTRUCTIONAL OBJECTIVE

STUDENT OUTCOME JUSTIFICATION

1. To Understand the flow through nozzle & diffuser with and without shock.

(a) An ability to apply knowledge of Mathematics, Science and

Engineering.

The Students are studying basic concepts, energy equations and working of nozzle and diffusers.

(c) an ability to design a system, component, or process to meet desired needs within realistic constraints such as economic,

environmental, social, political, ethical, health and safety,

The Students are able to design the components - nozzles and

diffusers - in compressible flow applications.

(e) An ability to identify, formulate and solve engineering problems.

The students are developing their ability to solve the engineering

flow problems in the nozzles and diffusers.

(a) An ability to apply knowledge of Mathematics, Science and

Engineering.

The students are studying the fluid flow properties due to friction and

heat transfer in flow through

(c) an ability to design a system, component, or process to meet

2. To Understand the flow desired needs within realistic The students are able to design the through constant area duct constraints such as economic, flow system in constant area duct using friction and heat environmental, social, political, applications such as in aircraft transfer. ethical, health and safety, engines.

manufacturability, and sustainability.

(e) An ability to identify, formulate and solve engineering problems.

The students are able to solve problems related to flow through constant area ducts with friction

and heat transfer.

a) An ability to apply knowledge of Mathematics, Science and The students are applying their

Engineering. science knowledge to study the flow through the compressors and

3.Design Calculations of all (e) An ability to identify, formulate turbines. types of turbines and their operations

and solve engineering problems.

(e) An ability to identify, fOlIDulate and solve engineering problems.

The students are able to study pelformance of and solve flow

problems related to compressors and turbines.

3.SYLLABUS

L T P C ME0302 GAS DYNAMICS AND TURBO MACHINERY 3 2 0 4

Prerequisite Thermodynamics and Fluid Mechanics

PURPOSE On completion of this course - the students will be in a position to apply their knowledge to solve problems in basic compressible flow, and all fluid machines working under the same principle. Only flow aspects of these Machines are considered and mechanical and material aspects are not included.

INSTRUCTIONAL OBJECTIVES The course aims at analysis of

1. Flow through nozzle and diffuser with and without shock

2. Flow through constant area duct using friction and heat transfer

3. Design calculations of all types ofturbines and their operations are covered

UNIT I FUNDAMENTALS OF COMPRESSIBLE FLOW AND FLOW THROUGH VARIABLE AREA DUCTS 9

Energy equation for compressible fluid flow, various regimes offlow, reference velocities stagnation states, velocity of sound derivation, critical states, Mach number, Crocco number, critical Mach number, types of waves, Mach cone, Mach angle, effect of Mach number on compressibility, equivalent of Bernoulli's equation for compressible flow.

Isentropic flow through variable area ducts, T-S and h-s diagrams for nozzles and diffusers, area ratio as a function of Mach number, impulse function (no derivation), mass flow rate through nozzles and diffusers, nondimensional mass flow rate in terms of pressure ratio (Flienger's formula).

UNIT II FLOW WITH NORMAL SHOCK 9 Development of shock wave, governing equations, variation of flow parameters like static pressure, static temperature, density, stagnation pressure and entropy across the shock (no derivations), Prandtl - Meyer equation, impossibility of shock in subsonic flows, strength of a shock wave, flow through nozzles and diffusers with shock, normal shock in Fanno and Rayleigh flows, (elementary treatment only).

UNIT III FLOW THROUGH CONSTANT AREA DUCTS 9 Flow in constant area ducts with friction (Fanno flow), Fanno curves and Fanno flow equations, variation of flow properties (no derivation), variation of Mach number with duct length. Flow in constant area duct with heat transfer (Rayleigh flow), Rayleigh curves and Rayleigh flow equations, variation of flow properties (no derivation), maximum heat transfer.

UNIT IV PRINCIPLES OF TURBOMACHINERY 9 Classification - specific work - representation of specific work in T-s and h-s diagrams - internal and external loses - Euler's equation of turbo Machinery - ideal and actual velocity triangles - slip and its estimation - impulses and reaction type Machines - degree of reaction - effect of outlet blade angles on blade shape - model laws, specific speed and shape number - special features of hydro, steam and gas turbines - performance characteristics ofturbo Machines - cavitation, surge and stall - thin aerofoil theory.

UNIT V STUDY OF TURBOMACHINES 9 Compressors - Axial and centrifugal type, Axial flow Turbines - Velocity triangles, performance (Elementary treatment only).

TUTORIAL 15 TOTAL 60

TEXTBOOKS

I.Yahya, S. M., Fundamentals ojCompressible Flow with Aircraft and Rocket Propulsion, Wiley Eastern, New Delhi, 1993

2.Yahya, S. M., Turbines, Fans and Compressors, Tata McGraw Hill Publications, New Delhi, 1996

REFERENCE BOOKS

l.Shapiro, A. H., The Dynamics and Thermodynamics ojCompressible Fluidflow - (Vol I and II), Ronald Press, New York, 1953

2. Gopalakrishnan, G. and Prithvi Raj, D., Treatise on Turbo Machines, Scitech Publications, Chennai, 2002

3.Dixon, S. L., Fluid Mechanics and Thermodynamics oj Turbo Machinery, Pergomen Publications, 1998.

4.SESSION PLAN

COURSE CODE/NAME : ME 0302 - GAS DYNAMICS AND TURBO MACHINERY YEAR / SEMESTER : III NI (Even 2013-2014 )

Session No.

No. of

Hrs

Topics TextlReference books

1 1

Fundamentals of compressible flow and flow through variable area ducts: Energy equations

T 1, chapter 2

2 1

Various regimes of flow, reference velocities, stagnation states, velocity of sound derivation

T 1, chapter 2

3 1

Critical states, Mach number, Crocco number, problems based on isentropic flow

TI, chapter 2

4 1

Types of waves - subsonic, sonic and supersonic waves. Mach cone, Mach angle

TI, chapter 2

5 1

Effect of Mach number on compressibility, equivalent of Bernoulli's equation for compressible flow.

TI, chapter 2

6 1 Problems in isentropic compressible flow Tl, chapter 2 7

1 Isentropic flow through variable area ducts: T-S and h-s diagrams for nozzles and diffusers

TI, chapter 4

8 1

Area ratio as a function of Mach number, Impulse function (no derivation)

TI, chapter 4

9 1

Mass flow rate through nozzles and diffusers, Problems based on flow through nozzles and diffusers

Tl, chapter 4

10 1 Mass flow rate in terms of pressure ratio (Flienger's formula) TI, chapter 2 11 1 Problems in variable area flow - nozzles TI, chapter 4 12 1 Problems in variable area flow - diffusers. TI, chapter 4 13 1 Flow with normal shock - Development, governing equations T 1, Chapter 6 14

1 Variation of flow parameters -static pressure & temperature, density, stagnation pressure and entropy across the shock (no derivations)

Tl, Chapter 6

15 1 Derivation ofPrandtl- Meyer equation Tl, Chapter 6 16 1 Impossibility of shock in subsonic flows, strength of a shock wave Tl, Chapter 6 17 1 Flow through nozzles with shock T 1, Chapter 6 18 1 Flow through diffusers with shock Tl, Chapter 6 19 1 Problems based on flow through nozzles with shock Tl, Chapter 6 20 1 Problems based on flow through diffusers with shock TI, Chapter 6 21 1 Problems - Supersonic wind tunnels involving normal shocks TI, Chapter 6 22 1 Normal shock in Fanno and Rayleigh flows (elementary treatment) T 1, Chapter 6 23 1 Problems in normal shock wave T 1, Chapter 6 24 1 Problems in wind tunnels with shocks. T 1, Chapter 6 25

1 Flow through constant area ducts: Flow in constant area ducts with friction (Fanno flow), Fanno curves

TI, Chapter 8

26 1 Fanno flow equations Tl, Chapter 8 27 1 Variation of flow properties (no derivation) TI, Chapter 8 28 1 Problems in Fanno flow Tl, Chapter 8 29 1 Variation of Mach number with duct length Tl, Chapter 8 30 1 Problems in Fanno flow involving duct length T 1, Chapter 8 31 1 Flow in constant area duct with heat transfer (Rayleigh flow & curves TI, Chapter 9 32 1 Rayleigh flow equations, flow properties (no derivation) T 1, Chapter 9 33 1 Problems in Rayleigh flow T 1, Chapter 9

34 1 Maximum heat transfer concept T1, Chapter 9 35 1 Problems in Rayleigh flow involving maximum heat transfer TI, Chapter 9 36 1 Problems - Fanno and Rayleigh flows. TI, Chapter 8,9 37 1 Principles of turbo machinery, classifications R2, Chapter 1,2 38

1 . Specific work, Representation of specific work in T-s and h-s diagrams, internal and external losses

R2, Chapter 1,2

39 1 Derivation ofEuler's equation of turbo machinery R2, Chapter 1,2 40 1 Ideal and actual velocity triangles - slip and its estimation R2, Chapter 1,2 41 1 Impulse and reaction type Machines R2, Chapter 1,2 42 1 Degree of reaction - effect of outlet blade angles on blade shape R2, Chapter 1,2 43 1 Model laws, specific speed and shape number R2, Chapter 1,2 44 1 Problems based on Model laws R2, Chapter 1,2 45 1 Special features of hydro, steam and gas turbines R2, Chapter 1,2 46 1 Performance characteristics, cavitation, surge and stall R2, Chapter 2,7 47 I Thin aerofoil theory. R2, Chapter 2,7 48 1 Problems involving velocity triangles. R2, Chapter 1,2 49 1 Study of turbo machines: Compressors - axial flow type R2, Chapter 5 50 1 Problems in axial flow compressors R2, Chapter 5 51 1 Compressors- centrifugal flow type R2, Chapter 4 52 1 Problems in centrifugal flow compressors R2, Chapter 4 53 1 Problems based on the performance of compressors R2, Chapter 4,5 54 1 Problems based on the performance of compressors R2, Chapter 4,5 55 1 Tutorial in axial and centrifugal flow compressor R2, Chapter 4,5 56 1 Axial flow turbines - velocity triangles R2, Chapter 8 57 1 Performance of axial flow turbines R2, Chapter 8 58 1 Problems based on the performance of turbines R2, Chapter 8 59 1 Problems in axial flow turbines. R2, Chapter 8 60 1 Problems in axial flow turbines. R2, Chapter 8

TEXTBOOKS T1. Yahya, S. M., Fundamentals of Compressible Flow with Aircraft and Rocket Propulsion, Wiley Eastern, New

Delhi, 1993. T2. Yahya, S. M., Turbines, Fans and Compressors, Tata McGraw Hill Publications, New Delhi, 1996.

REFERENCE BOOKS Rl. Shapiro, A. H., The Dynamics and Thermodynamics of Compressible Fluid flow - (Vol I and II), Ronald Press,

New York, 1953. R2. Gopalakrishnan,G.and Prithvi Raj,D., Treatise on Turbo Machines, Scitech Publications, Chennai, 2002. R3. Dixon, S. L., Fluid Mechanics and Thermodynamics of Turbo Machinery, Pergomen Publications, 1998.

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