The practical performance, both the efficiency and durability, of a high-pressure (HP) turbine depends on many interrelated factors, including both the steady and unsteady aerodynamics and the heat transfer characteristics. The aerodynamic performance of new turbine designs has traditionally been tested in large scale steady flow rigs, but the testing is adiabatic, and the measurement of heat transfer is very difficult. Transient facilities allow fully scaled testing with simultaneous heat transfer and aerodynamic performance measurements. The engine matched gas-to-wall temperature ratio simulates more closely the boundary layer and secondary flow development of the engine case. The short duration of the testing means that the blades are effectively isothermal with a rise of only a few degrees during a test. To isolate the aerodynamic losses, and thus the entropy generation due to the viscous losses, the entropy reduction due to heat transfer during the expansion needs to be determined. This entropy reduction is path dependent and requires knowledge of the full temperature and heat flux fields. This paper demonstrates a simple methodology for estimation of this entropy reduction, which allows the calculation of the adiabatic efficiency from the results of engine representative nonadiabatic testing. The methodology is demonstrated using a computational fluid dynamics (CFD) prediction which is validated against experimental heat flux data. Details of the other corrections required for transient test techniques such as unsteady leakage flows are also discussed.
Skip Nav Destination
e-mail: rog.ainsworth@stcatz.ox.ac.uk
Article navigation
November 2012
Research Papers
Turbine Aerodynamic Performance Measurement Under Nonadiabatic Conditions
Roger W. Ainsworth
Roger W. Ainsworth
Department of Engineering Science,
e-mail: rog.ainsworth@stcatz.ox.ac.uk
University of Oxford
, Oxford OX1 3PJ, UK
Search for other works by this author on:
Nicholas R. Atkins
Roger W. Ainsworth
Department of Engineering Science,
University of Oxford
, Oxford OX1 3PJ, UK
e-mail: rog.ainsworth@stcatz.ox.ac.uk
J. Turbomach. Nov 2012, 134(6): 061001 (8 pages)
Published Online: August 27, 2012
Article history
Received:
February 3, 2009
Revised:
July 29, 2011
Online:
August 27, 2012
Published:
August 27, 2012
Citation
Atkins, N. R., and Ainsworth, R. W. (August 27, 2012). "Turbine Aerodynamic Performance Measurement Under Nonadiabatic Conditions." ASME. J. Turbomach. November 2012; 134(6): 061001. https://doi.org/10.1115/1.4004857
Download citation file:
Get Email Alerts
Related Articles
Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration
J. Turbomach (January,2012)
Calculation of the Expansion Through a Cooled Gas Turbine Stage
J. Turbomach (July,2006)
Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part I: Experimental Approach
J. Turbomach (April,2008)
Rotor Blade Heat Transfer of High Pressure Turbine Stage Under Inlet Hot-Streak and Swirl
J. Eng. Gas Turbines Power (June,2015)
Related Proceedings Papers
Related Chapters
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
The Special Characteristics of Closed-Cycle Gas Turbines
Closed-Cycle Gas Turbines: Operating Experience and Future Potential