Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements
Kost, F. and Nicklas, M. (2001) Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements. In: ASME TURBO EXPO 2001. ASME TURBO EXPO 2001, New Orleans, USA, 4.-7. Juni 2001, New Orleans, USA.
Full text not available from this repository.
Thermodynamic and aerodynamic measurements were carried out in a linear turbine ascade ith transonic flow field. Heat transfer and adiabatic film-cooling effectiveness resulting from the interaction of the flow field and the ejected coolant at the endwall were measured and will be discussed in two parts. The investigations were performed in the Windtunnel for Straight Cascades (EGG) at DLR, Goettingen. The film-cooled NGV endwall was operated at representative nondimensional engine conditions regarding Mach and Reynolds number (Ma_2=1.0, Re_2=850,000). Part I of the investigations discusses the aerodynamic measurements. Detailed aerodynamic measurements were carried out in the vicinity of a turbine stator endwall using conventional pressure measurements and a Laser-2-Focus (L2F) device. The L2F served as a velocimeter measuring 2D-velocity vectors and turbulence quantities and as a tool to determine the concentration of coolant ejected through a slot and through holes at the endwall. Pressure distribution measurements provided information on the endwall pressure field and its variation with coolant flow rate. Pressure probe measurements delivered cascade performance data. Oil flow visualization and Laser velocimetry gave a picture of the near endwall flow field and its interference with the coolant. A strikingly strong interaction of coolant air and secondary flow field could be identified. The measurement of coolant concentration downstream of the ejection locations provided a detailed picture of the coolant flow convection and its mixing with the main flow. The relative coolant concentration in the flow field is directly comparable to the adiabatic film-cooling effectiveness measured by thermal methods at the wall.
|Document Type:||Conference or Workshop Item (Paper)|
|Title:||Film-Cooled Turbine Endwall in a Transonic Flow Field. Part I - Aerodynamic Measurements|
|Journal or Publication Title:||ASME TURBO EXPO 2001|
|Keywords:||Transonic flow, Turbine flow, Turbine platform, Endwall, Secondary Flow, Laser velocimetry, L2F, Coolant flow, Aerodynamic measurements, Film cooling effectiveness|
|Event Title:||ASME TURBO EXPO 2001, New Orleans, USA, 4.-7. Juni 2001|
|Event Location:||New Orleans, USA|
|Event Type:||international Conference|
|HGF - Research field:||Energy|
|HGF - Program:||Efficient Energy Conversion|
|HGF - Program Themes:||E VG - Combustion and Gas Turbine Technologies|
|DLR - Research area:||Energy|
|DLR - Program:||E VG - Combustion and Gas Turbine Technologies|
|DLR - Research theme (Project):||E - Gasturbine (old)|
|Institutes and Institutions:||Institute of Propulsion Technology|
|Deposited By:||elib DLR-Beauftragter|
|Deposited On:||16 Sep 2005|
|Last Modified:||06 Jan 2010 13:13|
Repository Staff Only: item control page