Comparison of Labyrinth Seal Calculation and Real Aircraft Turbine Engine Measurement

Abstract

This paper describes comparison between 3D CFD calculation of labyrinth seal of a turbine engine and measurement of actual advanced turbine engine in test facility. The goal is to verify capability of the 3D CFD modelling and obtain more insight into air flow path in the labyrinth seal. The total temperature was revealed not being a constant value through the labyrinth seal, thus driving design and even service trend monitoring consequences.

Labyrinth Seal Air Flow Investigation and Measurement Device Introduction

“…The total temperature difference is increasing with increasing rotational speed. The maximal difference between inlet and outlet temperature is approx.5.5 K. The value is not corresponding to that found in[11], where the temperature measurement was presented, because the RC is not comparable with previous researches.Figure12provides mass flow characteristic. Because there are no blades, the flow is a function of the pressure at inlet, outlet and critical area.…”

“…For the 3D CFD calculations the labyrinth seal model from [11] was used. In short, it is isolated labyrinth seal with radial clearance 𝑅𝐶 = 0.1 mm, rotational speed 𝑛 = 60000 min -1 , inlet pressure 𝑝 0 = 300 kPa, inlet total temperature 𝑇 0 = 288 K and turbulent model k-ε.…”

“…Based on the previous researches ( [4], [10] and [11]) it was decided to design new labyrinth seal measurement device in CASR. The reasons were two:…”

“…The article [9] introduced the stepped labyrinth seal measurement device and discharge coefficient calculation. The comparison between CFD calculation and real aircraft gas turbine measurement are in [10] and [11].…”