The gas turbine engine is a complex machine involving operation at extremes of pressure and temperature and demanding expertise at the highest level of engineering technology. Read more Read less

Concurrent engineering practices in industry demand from the individual a thorough appreciation of the interaction between the various gas path components of the gas turbine engine. In addition, interactions between aerodynamics, thermodynamics and mechanical integrity for a particular component must be thoroughly appreciated if an individual is to make a useful contribution in design and performance assessment.

At a glance

  • Duration5 days
  • LocationCranfield campus
  • Cost£1710.  The course fee includes refreshments and lunch during the day. Accommodation is not included and must be booked separately. Concessions available

Course structure

This 5-day course is presented through a mixture of lectures, tutorials and worked examples. Printed course material is provided for delegates use during and after the course. Active participation from the delegates is strongly encouraged particularly during the worked examples in order to consolidate learning. All delegates will receive a Certificate of Attendance upon completion of this course.

What you will learn

The course aims to present an in depth coverage of the key aspects of gas turbine component technologies and addresses aspects such as component design, characteristics and performance. On completion of this course, the delegate should be able to:

  • Understand the key engineering technologies which underpin the main gas turbine components.
  • Understand the basis of the design approaches for the engine gas path components and the impact of mechanical, aerodynamic and aerothermal constraints. 
  • Appreciate the aerodynamic and thermodynamic design aspect of the main elements as well as the computational methods used in current design.

Core content

  • Gas Turbine Fundamentals

A brief review of the fundamental fluid mechanics applied to the gas turbine engine; adiabatic and isentropic flow, static and stagnation conditions. Mass flow functions and choking.

  • Axial Compressor Design and Performance

Overall problems of diffusing air flow. The axial compressor stage, stage loading, diffusion parameters, flow coefficient, reaction. The overall stage characteristic, real and ideal, stall and choke. Radial Equilibrium considerations, design for free vortex, prescribed vortex, graded work, etc. The overall compressor characteristic, surge line, running line, effect of changes in inlet pressure and temperature. Off-Design performance, use of variable IGV's, air bleed, multi-spooling. Stage matching. Choice of annulus geometry, tip speed, etc. Compressor design tutorial.

  • Axial Turbine Design and Performance

Problems of expanding air flow and the importance of passage shape. Turbine architectures and layout. Choice of blade profile shape, prescribed velocity distribution. The axial turbine stage, velocity triangles, reaction, stage loading and flow coefficients; limiting values. The real and ideal characteristic. Design for maximum power, effect of Mach number, effect of choking and changes of inlet temperature and pressure. Factors affecting efficiency and correlations. Choice of design values according to application. Choice of overall annulus geometry and layout; rising line, constant mean diameter and falling line.

  • Blade Cooling

NGV and blade cooling, definition of terms, methods of cooling; impingement film and transpiration. The design compromise between aerodynamics, cooling and mechanical integrity.

  • Combustion Systems

Burning velocity; effects of pressure, temperature and turbulence. Methods of measuring burning velocity. Chemical reaction rates. Reaction rate parameters applicable to practical combustion systems.

Performance criteria of combustion chambers; combustion efficiency, stability and ignition performance, temperature traverse quality. Design criteria; determination of chamber dimensions and pressure loss to meet stipulated performance requirements. Relative merits of tubular, annular and tubo-annular chambers.

Fuel injection methods; spray injection, vaporising tubes, airblast atomisers. Combustion chamber aerodynamics; diffuser characteristics, influence of inlet velocity profile on pressure loss and temperature traverse quality.

Problems of ground starting and altitude re lighting. Relative merits of weak, stoichiometric and rich primary zones.

  • Mechanical Integrity

Origin of loads on gas-turbine components. Factors and strength criteria for proof, ultimate, creep, fracture and fatigue cases. Integrity of specific components such as discs, blades, shafts, combustion chambers, casings, flanges, etc. Cumulative creep, effect of mean stress, surface conditions and stress concentration on fatigue. Cumulative fatigue, double-Goodman diagram and rainflow methods. Examples of finite-element analysis.

Fatigue and Fracture Mechanics - two parts of the same process. Griffith Criterion for fracture. The stress analysis approach. Fracture Toughness in plane strain and plane stress. Geometric and flaw shape effects. Effects of cyclic loading. Paris Law, mean stress effects. Threshold Stress Intensity, Environmental effects. Practical Examples - discs, rolling contact bearings. Types of vibration encountered in the gas turbine. Blade modes of vibration, including centrifugal and thermal effects. Analytical and experimental methods of determining natural frequencies, holography, laser-doppler, etc. Production of frequency diagram and methods of overcoming vibration problems. Disc vibration with transfer matrix solution. Critical speeds of shafts and alleviation by means of squeeze-film damper bearings.

  • CFD for Gas Turbines

An overview of the numerical methods that can be employed for prediction of the flows in gas turbine components. The understanding of the opportunities and limitations that apply to these methods is important whether one wishes to become a CFD practitioner or is placed downstream of those who run these codes.

Who should attend

The course will be of interest to new, and experienced, engineers who expect to be, or are already, closely involved in engine design or performance evaluation in the gas turbine manufacturing or user industries. The course will also be of value to more experienced engineers in the gas turbine sector who have a need for an overview of the design and performance of the main engine component technologies beyond their recent experience.

Speakers

The course is presented through lectures and tutorials conducted by members of Cranfield University’s staff all of whom have considerable academic and industrial experience. Additional lectures will be presented by senior engineers from industry.

Concessions

Where more than five delegates are booking from within one site of one organisation, a discount of 10% will apply to the invoice for the course tuition fee. Accommodation fees are not included in the discount scheme at time of booking.

Accommodation options and prices

This course is non-residential. If you would like to book accommodation on campus, please contact Mitchell Hall or Cranfield Management Development Centre directly. Further information about our on campus accommodation can be found here.  Alternatively you may wish to make your own arrangements at a nearby hotel. 

Location and travel

Cranfield University is situated in Bedfordshire close to the border with Buckinghamshire. The University is located almost midway between the towns of Bedford and Milton Keynes and is conveniently situated between junctions 13 and 14 of the M1.

London Luton, Stansted and Heathrow airports are 30, 90 and 90 minutes respectively by car, offering superb connections to and from just about anywhere in the world. 

For further location and travel details

Location address

Cranfield University
College Road
Cranfield
Bedford 
MK43 0AL

How to apply

Read our Professional development (CPD) booking conditions.