EXPERIMENTAL STUDY ON REDUCTION OF TIP LEAKAGE LOSS IN ULTRA HIGHLY LOADED LINEAR TURBINE CASCADE : EFFECTS OF INCIDENCE ANGLE ON OPTIMUM SQUEALER DEPTH [PDF]
, 2019 In this study, the squealer tip was applied to the ultra-highly loaded turbine cascade (UHLTC) with the turning angle of 160 degrees. The detailed internal flow measurements by using the 5-hole Pitot tube and oil flow visualisations were conducted for ...
秋山 浩二
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Energy efficient engine high-pressure turbine detailed design report [PDF]
The energy efficient engine high-pressure turbine is a single stage system based on technology advancements in the areas of aerodynamics, structures and materials to achieve high performance, low operating economics and durability commensurate with ...
Howe, D. C. +2 more
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State College Times, February 17, 1933 [PDF]
, 1933 Volume 21, Issue 71https://scholarworks.sjsu.edu/spartandaily/12839/thumbnail ...
San Jose State University, School of Journalism and Mass Communications
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Effect of unsteady wake, free stream turbulence, tip geometry on blade tip flow and heat transfer [PDF]
, 2003 A comprehensive investigation of the effect of various tip sealing geometries is presented on the blade tip leakage flow and associated heat transfer.
Saxena, Vikrant
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Analysis of Unsteady Tip and Endwall Heat Transfer in a Highly Loaded Transonic Turbine Stage [PDF]
In a previous study, vane-rotor shock interactions and heat transfer on the rotor blade of a highly loaded transonic turbine stage were simulated. The geometry consists of a high pressure turbine vane and downstream rotor blade. This study focuses on the
Ameri, Ali +2 more
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超高負荷タービン直列翼列の漏れ損失の低減に関する実験的研究：スキーラの適用と深さの影響 [PDF]
, 2017 An increase of turbine blade loading by the increase of blade turning angle enables to reduce a gas turbinein size and weight by decreasing the number of turbine blades and stages.
高倉 健介
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Advanced ceramic material for high temperature turbine tip seals [PDF]
Forty-one material systems were evaluated for potential use in turbine blade tip seal applications at 1370 C. Both ceramic blade tip inserts and abradable ceramic tip shoes were tested.
Solomon, N. G. +2 more
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Aero-thermal characteristics and film cooling of transonic turbine blade tips [PDF]
, 2019 Film cooling is essential to protect high pressure turbine blade tips from the high speed, high temperature overtip leakage flows, which are forced through the tip clearance gap. Careful design of the blade tip and cooling strategy is necessary to reduce
Saul, Andrew
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A performance/loss evaluation of SSME HPFTP turbine [PDF]
An evaluation of component losses of the High Pressure Fuel Turbopump (HPFTP) in the Space Shuttle Main Engine (SSME) is performed using a mean-line prediction method.
Chyu, Mingking K.
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Numerical Investigations of Flow and Film Cooling with Endwall Contouring and Blade Tip Ejection under Rotating Turbine Conditions [PDF]
, 2015 An effort is made to numerically study the impact of rotating turbine conditions on the aerodynamic performance, film cooling effectiveness and heat transfer with the application of the endwall contouring and blade tip ejection.
Lu, Kun
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