Author: Tibor Kiss
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 582
Book Description
Experimental and Numerical Investigation of Transonic Turbine Cascade Flow
Author: Tibor Kiss
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 582
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 582
Book Description
Experimental and Numerical Investigation of Turbine Cascade Flow
Author: V. Michelassi
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Experimental and Numerical Investigation of Boundary-layer and Wake Development in a Transonic Turbine Cascade
Author: Vittorio Michelassi
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
Book Description
Experimental and Numerical Study of Transonic Turbine Cascade Flow
Author: Tibor Kiss
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Experimental investigation of the flow field downstream of a plane turbine cascade in transonic flow
Author: R. Kiock
Publisher:
ISBN:
Category :
Languages : de
Pages : 38
Book Description
Publisher:
ISBN:
Category :
Languages : de
Pages : 38
Book Description
Experimental Analysis Data on the Transonic Flow Past a Plane Turbine Cascade
Author: M. Šťastný
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 0
Book Description
The paper presents results from aerodynamic tests on a transonic rotor turbine profile cascade, including interferograms of the flow field and aerodynamic data measured downstream from the cascade. The dimensions and aerodynamic data on the cascade are given in detail. Analysis following the experimental data collection was aimed at investigating the sensitivity of transonic flow in the vicinity of the throat and related conditions leading to the compression effect. Further, the development of the flow structure and the cascade parameters over a wide range of exit Mach numbers, as well as incidence angles are shown. The experimental data are compared with results of calculations based on mathematical models.
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 0
Book Description
The paper presents results from aerodynamic tests on a transonic rotor turbine profile cascade, including interferograms of the flow field and aerodynamic data measured downstream from the cascade. The dimensions and aerodynamic data on the cascade are given in detail. Analysis following the experimental data collection was aimed at investigating the sensitivity of transonic flow in the vicinity of the throat and related conditions leading to the compression effect. Further, the development of the flow structure and the cascade parameters over a wide range of exit Mach numbers, as well as incidence angles are shown. The experimental data are compared with results of calculations based on mathematical models.
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Experimental and Numerical Validation of the Flow and Heat Transfer on a Transonic Turbine Blade
Author: Jacques Emile De Villiers
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 330
Book Description
Publisher:
ISBN:
Category : Cascades (Fluid dynamics)
Languages : en
Pages : 330
Book Description
Experimental and Numerical Studies of Unsteady Heat Transfer in a Transonic Turbine
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The effects of a shock wave passing through a blade passage on surface heat transfer to turbine blades were measured experimentally. The experiments were performed in a transonic linear cascade which matched engine Reynolds number, Mach number, and shock strength. Unsteady heat flux measurements were made with Heat Flux Microsensors on both the pressure and suction surfaces of a single blade passage. Unsteady static pressure measurements were made using Kulite pressure transducers on the blade surface and end wails of the cascade. The experiments were conducted in a stationary linear cascade of blades with heated transonic air flow using a shock tube to introduce shock waves into the cascade. A time-resolved model based on conduction in the gas was found to accurately predict heat transfer due to shock heating measured during experimental tests without flow. The model under-predicted the experimental results with flow, however, by a factor of three. The heat transfer increase resulting from shock passing in heated flow averaged over 200 us (typical blade passing period) was found to be a maximum of 60% on the pressure surface near the leading edge. Based on experimental results at different flow temperatures, it was determined that shock heating has the primary effect on heat transfer, while heat transfer increase due to boundary layer disturbance is small.
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
The effects of a shock wave passing through a blade passage on surface heat transfer to turbine blades were measured experimentally. The experiments were performed in a transonic linear cascade which matched engine Reynolds number, Mach number, and shock strength. Unsteady heat flux measurements were made with Heat Flux Microsensors on both the pressure and suction surfaces of a single blade passage. Unsteady static pressure measurements were made using Kulite pressure transducers on the blade surface and end wails of the cascade. The experiments were conducted in a stationary linear cascade of blades with heated transonic air flow using a shock tube to introduce shock waves into the cascade. A time-resolved model based on conduction in the gas was found to accurately predict heat transfer due to shock heating measured during experimental tests without flow. The model under-predicted the experimental results with flow, however, by a factor of three. The heat transfer increase resulting from shock passing in heated flow averaged over 200 us (typical blade passing period) was found to be a maximum of 60% on the pressure surface near the leading edge. Based on experimental results at different flow temperatures, it was determined that shock heating has the primary effect on heat transfer, while heat transfer increase due to boundary layer disturbance is small.
A Numerical Investigation of Time Resolved Flows Around Turbine Blades
Author: Edward J. Brooksbank
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description