Transonic turbine blade cascade testing facility Download PDF EPUB FB2
The transonic low pressure turbine (LPT) linear cascade facility has been recently commissioned at the ARC to allow detailed measurements of fluid dynamics phenomena in a high-speed turbine passage. The transonic wind tunnel operates in blow-down mode using high pressure air supplied from large high pressure reservoirs and exhausts to ambient.
Get this from a library. Transonic turbine blade cascade testing facility. [Vincent G Verhoff; William P Camperchioli; Isaac Lopez; United States.
Army Aviation Systems Command.; United States. National Aeronautics and Space Administration.]. Transonic turbine blade cascade testing facility [microform] / Vincent G.
Verhoff and William P. Camperchioli and Isaac Lopez National Aeronautics and Space Administration ; US Army Aviation Systems Command ; For sale by the National Technical information Service [Washington, DC: St.
Louis, Mo.]: [Springfield, Va Australian/Harvard Citation. Transonic turbine vane tests in a new miniature cascade facility Article (PDF Available) in Proceedings of the Institution of Mechanical Engineers Part A Journal of Power and Energy (5) single blade in a linear cascade oscillating in a generic three-dimensional flex mode and showed that the local pressure response was heavily non-linear.
The present facility ties up with the previous results and has been designed to investigate the aeroelastic behavior of a low pressure turbine cascade in a realistic environment. The cascade is. Turbine blade endwall heat transfer measurements are presented for a range of Reynolds and Mach numbers.
Data were obtained for Reynolds numbers based on inlet conditions of and × 10 6, for isentropic exit Mach numbers of andand for free-stream turbulence intensities of and were conducted in a linear cascade at the NASA Cited by: An overview of the recent facility modifications to NASA’s Transonic Turbine Blade Cascade Facility and aerodynamic measurements on the VSPT incidence-tolerant blade are presented.
This work supports the development of variable-speed power turbine (VSPT) speed-change technology for the NASA Large Civil Tilt Rotor (LCTR) : Ashlie B. McVetta, Paul W.
Giel. This facility is driven by a compressor station of 3 MW power and allows testing of transonic gas turbine stages in full flow similarity. The test stand gives access of conventional pressure and temperature probes as well as of optical measurement devices such as Laser-Doppler-Velocimetry (LDV) and Particle-Image-Velocimetry (PIV) systems.
The present work summarizes the design process of a new continuous closed-loop hot transonic linear cascade. The facility features fully modular design which is intended to serve as a test bench for axial microturbomachinery components in independently varying Mach and Reynolds numbers ranges of 0– and 2 × 10 4 –6 × 10 5, : Eli Yakirevich, Ron Miezner, Boris Leizeronok, Beni Cukurel.
Transonic Turbine Blade Cascade. The Transonic Turbine Blade Cascade facility can match engine conditions through pertinent flow parameters such as the Reynolds number, the Mach number, and the inlet turbulence levels.
Future high-pressure turbines will eliminate blade rows by producing higher loading on a single stage. Fig. 1 Transonic Test-Turbine Facility flow scheme Fig. 2 Transonic Test Turbine Facility section The air compressed through this machine can be used for driving the test turbine if the pressure ratio is lower than approximately 4 and the running speed of the stage to be tested is high enough.
Through the. inlet conditions. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with of turning and an axial chord of cm.
The flow field in the cascade is highly three dimensional as a result of thick boundary layers at the test section inlet. End wall heat. Erhard J, " Design, Construction and Commissioning of a Transonic Test-Turbine Facility, " Doctoral Thesis at the Institute of Thermal Turbomachinery and. Impact of Flow Quality in Transonic Cascade Wind Tunnels: Measurements in an HP Turbine Cascade one chord length upstream of the blade leading edge.
The inlet static taps cover the whole cas-cade width. The taps have a spacing of mm, giving four taps per blade pitch. Fig. 3 Cascade blade row measurement locations (Adapted from Jouini et al. Blade Heat Transfer Measurements and Predictions in a Transonic Turbine Cascade NASA/TM— August ARL–TR– U.S.
ARMY RESEARCH LABORATORY. The NASA STI Program Office in Profile Since its founding, NASA has been dedicated to the advancement of aeronautics and space. Two-Dimensional Cascades Introduction The design and performance prediction of axial flow compressors and turbines has been based, in the main, upon measurements of the flow-through two-dimensional cascades of blades.
However, to an increasing extent, computational fluid dynamic (CFD) methods are now being used to simulate cascade testing.
This paper presents an aerodynamic optimum design method for transonic turbine cascades based on the Genetic Algorithms coupled to the inviscid flow Euler solver and the boundary-layer calculation. The Genetic Algorithms control the evolution of a population of cascades towards an optimum design.
The fitness value of each string is evaluated using the Cited by: Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility.
The test article was a turbine rotor with deg of turning and an axial chord of cm. The large scale allowed for very detailed measurements of both flow field and surface more».
Numerical modeling of transonic centripetal turbulent flow in radial blade cascade is described in this paper. Attention is paid to effect of the outlet confusor on flow through the radial blade cascade. Parameters of presented radial blade cascade are Cited by: 1.
In Section 2, time-resolved film cooled turbine rotor heat transfer measurements are compared with numerical predictions. Data were taken on a fully film cooled blade in a transonic, high pressure ratio, single-stage turbine in a short duration turbine test facility, which simulates full-engine non-dimensional conditions.
A turbine (from the Latin turbo, a vortex, related to the Greek τύρβη, tyrbē, meaning "turbulence") is a rotary mechanical device that extracts energy from a fluid flow and converts it into useful work produced by a turbine can be used for generating electrical power when combined with a generator.
A turbine is a turbomachine with at least one moving part called a rotor. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Heat Transfer and Flow Characteristics on the Rotor Tip and Endwall Platform Regions in a Transonic Turbine Cascade Allan N.
Arisi ABSTRACT This dissertation presents a detailed experimental and numerical analysis of the aerothermal characteristics of the turbine extremity regions i.e. the blade tip and endwall regions.
I’m trying to replicate the transonic, inviscid results of an inverse turbine blade design thesis. I have the original blade geometry, and have more or less copied the original mesh.
The original geometry is discontinuous, leading to a passage shock at the discontinuity (I’ve attached geometry and Mach contour images). Abstract.
A cylindrical section of the last stage of a gas turbine blade has been investigated experimentally in an annular non-rotating cascade facility as regards to its steady-state and time-dependent aerodynamic characteristics for off-design inlet and transonic outlet flow conditions at realistic reduced by: 5.
low speed passing bar linear cascade facility was previously documented by Banieghbal et. al, (). It is the aim of this paper to describe the high speed rotating bar linear cascade facility and to compare it with its low speed counterpart. Transonic cascade facility The high speed experiments were carried out.
The Blade Test Facility (BTF) at Clarkson University was established as part of the Center for Evaluation of Clean Energy Technologies (CECET), an Intertek Company. Combined with funding from the New York State Energy Research and Development Authority (NYSERDA) to support and grow New York based wind market activities through performance testing, research and.
the unsteady ﬂow through an annular turbine cascade, the transonic Standard Test Case 4, Test Computations are performed on a two- and three-dimensional model of the blade row with either the Euler or the Navier-Stokes ﬂow models.
Results are compared to the experimental measurements. Comparisons of the unsteady surface pressure and the. Design of turbine cascades with transitional profile boundary layers Gabriel Acacio Alarcon Iowa State University Follow this and additional works at: Part of theMechanical Engineering Commons, and theOil, Gas, and Energy Commons.
This linear cascade of blades comprises a number of identical blades, equally spaced and parallel to one another. Figure (b) shows the test section of a cascade facility for transonic and moderate supersonic inlet velocities.
The upper wall is slotted and equipped for suction, allowing operation in the transonic regime. This paper presents a focusing schlieren system designed for the investigation of transonic turbine tip-leakage flows. In the first part, the functional principle and the design of the system are presented.
Major design considerations and necessary trade-offs are discussed. The key optical properties, e.g., depth of focus, are verified by means of a simple bench : Maximilian Passmann, Stefan aus der Wiesche, Franz Joos.Aero-thermal investigation of a highly loaded transonic linear turbine guide vane cascade: a test case for inviscid and viscous flow computations.
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