Highly Loaded Low-Pressure Turbine: Design, Numerical and Experimental Analysis (Preprint)
Abstract
The performance and detailed flow physics of a highly loaded, transonic, low-pressure turbine stage has been investigated numerically and experimentally. The mean rotor Zweifel coefficient was 1.35, with a work coefficient of 2.8, and a total pressure ratio of 1.75. The aerodynamic design was based on recent developments in boundary layer transition modeling. Steady and unsteady numerical solutions were used to design the blade geometry as well as to predict the design and off-design performance. Measurements were acquired in a recently developed, high-speed, rotating turbine facility. The nozzle-vane only and full stage characteristics were measured with varied mass flow, Reynolds number, and free-stream turbulence. The efficiency calculated from torque at the design speed and pressure ratio of the turbine was found to be 90.6%. This compared favorably to the meanline target value of 90.5%. This paper will describe the measurements and numerical solutions in detail for both design and off-design conditions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2010
- Accession Number
- ADA522186
Entities
People
- J. P. Clark
- J. T. Schmitz
- P. J. Koch
- Rong Ma
- S. C. Morris
- S. L. Puterbaugh
- T. C. Corke
Organizations
- Air Force Research Laboratory