NUMERICAL INVESTIGATION OF FREESTREAM LOW-PRESSURE TURBINE PASSAGE
Abstract
By increasing the low-pressure turbine (LPT) blade loading, significant cost savings and performance improvements can be realized for high-bypass ratio turbofan engines. The flow through the LPT is characterized by high freestream turbulence (FST) and low-Reynolds number conditions. How FST affects the end-wall flow physics and total pressure losses for front-loaded high-lift LPT blades is poorly understood. The main objectives of the proposed research are to (1) investigate and quantify the effect of FST on the total pressure losses and to develop a detailed understanding of the underlying flow physics; and (2) contribute to the existing knowledge of the effect of FST on the mid-span laminar separation from the suction surface. A combined investigative approach of implicit large-eddy simulations (ILES), advanced data analyses, and stability investigations will be employed to meet the research objectives. The flow through a linear LPT cascade with L2F research blades and end-wall will be simulated. The cascade geometry, mean flow, and FST characteristics will be matched to those of experiments at the Air Force Research Lab to allow for a direct validation of the simulations with available measurements.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 07, 2023
- Source ID
- FA95502210195
Entities
People
- Andreas Gross
Organizations
- Air Force Office of Scientific Research
- New Mexico State University
- United States Air Force