Experimental and numerical investigation of optimized blade tip shapes-part i: Turbine rainbow rotor testing and CFD methods

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F18%3A00349632" target="_blank" >RIV/68407700:21220/18:00349632 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1115/GT2018-76564" target="_blank" >https://doi.org/10.1115/GT2018-76564</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1115/GT2018-76564" target="_blank" >10.1115/GT2018-76564</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Experimental and numerical investigation of optimized blade tip shapes-part i: Turbine rainbow rotor testing and CFD methods

Popis výsledku v původním jazyce

Blade tip design and tip leakage flows are crucial aspects for the development of modern aero-engines. The inevitable clearance between stationary and rotating parts in turbine stages generates high-enthalpy unsteady leakage flows that strongly reduce the engine efficiency and can cause thermally induced blade failures. An improved understanding of the tip flow physics is essential to refine the current design strategies and achieve increased turbine aerothermal performance. However, while past studies have mainly focused on conventional tip shapes (flat tip or squealer geometries), the open literature suffers from a shortage of experimental and numerical data on advanced blade tip configurations of unshrouded rotors. This work presents a complete numerical and experimental investigation on the unsteady flow field of a high-pressure turbine, adopting three different blade tip profiles. The aerothermal characteristics of two novel high-performance tip geometries, one with a fully contoured shape and the other presenting a multicavity squealer-like tip with partially open external rims, are compared against the baseline performance of a regular squealer geometry. In the first part of this work, we describe the experimental setup, instrumentation and data processing techniques used to measure the unsteady aerothermal field of multiple blade tip geometries using the rainbow rotor approach. We report the timeaverage and time-resolved static pressure and heat transfer measured on the shroud of the turbine rotor.

Název v anglickém jazyce

Experimental and numerical investigation of optimized blade tip shapes-part i: Turbine rainbow rotor testing and CFD methods

Popis výsledku anglicky

Blade tip design and tip leakage flows are crucial aspects for the development of modern aero-engines. The inevitable clearance between stationary and rotating parts in turbine stages generates high-enthalpy unsteady leakage flows that strongly reduce the engine efficiency and can cause thermally induced blade failures. An improved understanding of the tip flow physics is essential to refine the current design strategies and achieve increased turbine aerothermal performance. However, while past studies have mainly focused on conventional tip shapes (flat tip or squealer geometries), the open literature suffers from a shortage of experimental and numerical data on advanced blade tip configurations of unshrouded rotors. This work presents a complete numerical and experimental investigation on the unsteady flow field of a high-pressure turbine, adopting three different blade tip profiles. The aerothermal characteristics of two novel high-performance tip geometries, one with a fully contoured shape and the other presenting a multicavity squealer-like tip with partially open external rims, are compared against the baseline performance of a regular squealer geometry. In the first part of this work, we describe the experimental setup, instrumentation and data processing techniques used to measure the unsteady aerothermal field of multiple blade tip geometries using the rainbow rotor approach. We report the timeaverage and time-resolved static pressure and heat transfer measured on the shroud of the turbine rotor.

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2018

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, Volume 5B: Heat Transfer

ISBN

978-0-7918-5109-8

ISSN

—

e-ISSN

—

Počet stran výsledku

15

Strana od-do

—

Název nakladatele

American Society of Mechanical Engineers - ASME

Místo vydání

New York

Místo konání akce

Lillestrom

Datum konání akce

11. 6. 2018

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

000456908500012