Blade stacking and clocking effects in two-stage high-pressure axial turbine

Abstract

Purpose

The purpose of this paper is to characterize the blade–row interaction and investigate the effects of axial spacing and clocking in a two-stage high-pressure axial turbine.

Design/methodology/approach

Flow simulations were performed by means of Ansys-CFX code. First, the effects of blade–row stacking on the expansion performance were investigated by considering the stage interface. Second the axial spacing and the clocking positions between successive blade–rows were varied, the flow field considering the frozen interface was solved, and the flow interaction was assessed.

Findings

The axial spacing seems affecting the turbine isentropic efficiency in both design and off-design operating conditions. Besides, there are differences in aerodynamic loading and isentropic efficiency between the maximum efficiency clocking positions where the wakes of the first-stage vanes impinge around the leading edge of the second-stage vanes, compared to the clocking position of minimum efficiency where the ingested wakes pass halfway of the second-stage vanes.

Research limitations/implications

Research implications include understanding the effects of stacking, axial spacing and clocking in axial turbine stages, improving the expansion properties by determining the adequate spacing and locating the leading edge of vanes and blades in both first and second stages with respect to the maximum efficiency clocking positions.

Practical implications

Practical implications include improving the aerodynamic design of high-pressure axial turbine stages.

Originality/value

The expansion process in a two-stage high-pressure axial turbine and the effects of blade–row spacing and clocking are elucidated thoroughly.

Citation

Touil, K. and Ghenaiet, A. (2019), "Blade stacking and clocking effects in two-stage high-pressure axial turbine", Aircraft Engineering and Aerospace Technology, Vol. 91 No. 8, pp. 1133-1146. https://doi.org/10.1108/AEAT-03-2018-0110