Design and Performance of the Axial Turbine Component of Gas Turbine Engines
Course date: 04 Nov 2013 - 08 Nov 2013
A thorough understanding of the role of the turbine component is important to those involved in the design and/or performance assessment of gas turbine engines. In particular, modern concurrent engineering practices demand a thorough appreciation of the interaction between aerodynamics, blade cooling and mechanical integrity requirements. In addition, the engineer must understand the compromises and limitations imposed on the turbine design and performance by the device it is driving, namely, the fan, the compressor or the external load.
Cranfield University is located at the very heart of the UK – within the innovation triangle between London and the cities of Oxford and Cambridge.
Our central location provides easy access from the M1, excellent main line rail service as well as proximity to key international airports. Set in rolling countryside, Cranfield offers a rich, rural landscape complemented by thriving towns and picturesque villages.
- Road: We are just 10 minutes from Junctions 13 & 14 of the M1 motorway. There is free parking on campus.
- Rail: Milton Keynes or Bedford
- Air: London Luton (22 miles), Heathrow (50 miles) or Birmingham (70 miles).
The course fee includes refreshments and lunch during the day.
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 is on a full-board basis from the evening before the course commences until the afternoon of the last day. The course fee includes refreshments and lunch during the day. The accommodation fee includes all other meals. Details of accommodation will be provided in the delegate information pack.
How to register
For more information on this course or booking details please contact:
Power and Propulsion short courses
T: + 44 (0) 1234 754683
On completion of the course, the delegate should be able to:
- select an appropriate shape and geometry for the turbine annulus diagram.
- select the number of stages needed for a given overall power requirement according to engine application.
- assess the design interactions between aerodynamic, mechanical integrity and blade cooling requirements.
- undertake preliminary design optimisation for both high pressure and low pressure turbines.
Who should attend
The course is structured to provide design and performance expertise for graduates or equivalent who will be closely involved in turbine design in the gas turbine manufacturing industry. The course is also ideally structured to suit the needs of graduate trainees whose final specialisation will require a good understanding of the role of the turbine in the engine.
The course will also be of value to experienced engineers in the manufacture or user industries who have a need for a detailed overview of axial turbine design and performance.
The role of the turbine within the engine. Selection of overall annulus geometry and layout; rising line, constant mean diameter and falling line.
The importance of blade passage shape, direct and indirect methods of design, prescribed velocity distribution. Choice of base profile shape. Mass flow limitations due to choking, limitations imposed on back surface deflection through blade cooling constraints. Choice of blade numbers and aspect ratio: Zweiffel’s and alternative lift coefficients, profile losses, cascade correlations effect of Mach number.
Basic stress loads, thermal stresses, multi-axial deformation and failure criteria. Characteristics of failure modes. Creep and life prediction. Vibrations and vibration criteria for design.
Turbine design example
A complete hand worked high pressure turbine aerodynamic design is carried out for both low and high turbine entry temperature cases to represent industrial and aeronautical applications, respectively. This is a fully interactive session involving extensive use of Q-curves. The results are analysed and discussed. A downstream low pressure turbine design solution is reviewed and a computer based optimisation of this undertaken to properly match the hp/lp turbine combination.
Choice of stage loading and flow coefficients according to engine role and overall performance requirements. The overall turbine performance characteristic. Hub to casing design and choice of vortex flow.
Velocity triangles, reaction, stage loading, flow coefficients. Design for maximum power, effect of choking and change of inlet temperature and pressure. Turbine isentropic and polytropic efficiency, effects of overtip leakage. Efficiency correlations. Limitations on exit hub/tip ratio.
Review of heat transfer principles and physical significance of non-dimensional groupings. Blade row boundary layers, external heat transfer coefficient distribution, effect of turbulence. Root cooled blades and NGVs, analytical and numerical methods of determining spanwise temperature distribution. Cooling efficiency, effectiveness and mass flow function: application at project design stage for determining metal and cooling air temperatures. Methods for optimising. Relative performance of convection, impingement, film, transpiration and liquid cooling.
Gas Turbine Engineering Courses
The Department of Power and Propulsion offers one of the largest gas turbine engineering training course portfolios for industry. For several years, our academics and network of industrial experts have welcomed delegates from all over the world to Cranfield.