cavity and leaking flows; high-speed LPT; measurement techniques; rig modification; transonic turbine; turbine blade and measurement advancements; Cavity and leaking flow; High Speed; High-speed low-pressure turbine; Low-pressure turbines; Measurement techniques; Rig modification; Transonic turbine; Turbine blade; Turbine blade and measurement advancement; Turbine stages; Mechanical Engineering
Abstract :
[en] This paper presents the commissioning of a newly designed High-Speed Low-Pressure Turbine (LPT) stage, operating at transonic exit Mach numbers and low Reynolds numbers, typical of modern geared turbofan (GTF) applications. The work falls within the scope of the Clean Sky 2 project SPLEEN (Secondary and Leakage Flow Effects in High-speed Low-pressure Turbines), which consists of an extensive experimental characterization of LPTs for GTFs. Geometries and measurements will constitute a valuable openaccess database for the validation of simulation methods and data analysis tools. At first, the characteristics of the research turbine are illustrated. The LPT stage is designed with an equal number of stationary vanes and shrouded rotor blades. The upstream and downstream hub cavities are purged and feature engine-realistic rim seals. The nominal operating condition of the stage is reported, along with a set of off-design conditions, obtained by varying rotor speed and purge mass flows. The second part of the paper describes the substantial revamping of the CT3 large-scale compression tube at Von Karman Institute for Fluid Dynamics, traditionally employed for high-pressure turbine testing, now adapted to host a high-speed LPT stage. The third section is an overview of the time-averaged and fast-response instrumentation. The test article is heavily instrumented, to maximize the amount of acquired data, while minimizing the number of blowdown tests. The dataset for each operating conditions includes aerothermal measurements in the annulus flow, in the hub cavities and in the shroud labyrinth seal. In addition, this section presents the design of an in-house traversing system for continuous probe traversing during the test. Finally, the outcome of the commissioning phase is discussed, with particular emphasis on the operating conditions stability, as well as on the inlet and cavity injection uniformity. The commissioning of a traversing system for continuous probe traversing during the shortduration test is also discussed.
Torre, Antonino Federico Maria ; Université de Liège - ULiège > Aérospatiale et Mécanique (A&M) ; Department of Turbomachinery and Propulsion, von Karman Institute for Fluid Dynamics, Rhode Saint-Genése, Belgium
Merli, Filippo; Department of Turbomachinery and Propulsion, von Karman Institute for Fluid Dynamics, Rhode Saint-Genése, Belgium
Da Valle, Lorenzo ; Université de Liège - ULiège > Aérospatiale et Mécanique (A&M) ; Department of Turbomachinery and Propulsion, von Karman Institute for Fluid Dynamics, Rhode Saint-Genése, Belgium
Patinios, Marios; Department of Turbomachinery and Propulsion, von Karman Institute for Fluid Dynamics, Rhode Saint-Genése, Belgium
Lavagnoli, Sergio ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Design of Turbomachines ; Department of Turbomachinery and Propulsion, von Karman Institute for Fluid Dynamics, Rhode Saint-Genése, Belgium
H2020 - 820883 - SPLEEN - Secondary and Leakage Flow Effects in High-SPeed Low-PrEssurE TurbiNes
Name of the research project :
SPLEEN project by the Clean Sky 2
Funders :
EU - European Union
Funding text :
The authors gratefully acknowledge funding of the SPLEEN
project by the Clean Sky 2 Joint Undertaking under the European
Union’s Horizon 2020 research and innovation program under
Grant Agreement 820883.
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