The determination of a three-dimensional turbomachinery blade configuration has always been a bottleneck in the design process. It is one of the major steps that require continuous improvement. The purpose of this paper is to describe the new parametric design approach that uses minimum key airfoil sectional parameters in turbine blade design. These parameters are camber line angles at leading edge (LE) and trailing edge (TE), radius at LE and TE, wedge angles at LE and TE, maximum thickness and its location along the camber line. The theory of the parametric design method will be discussed in detailed in the paper. A known multistage turbine configuration is used as an example to demonstrate the robustness of the present method.
|Number of pages||8|
|Journal||Transactions of the Aeronautical and Astronautical Society of the Republic of China|
|Publication status||Published - 1999 Sep|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering