Axial Turbine Blade Tips: Function, Design, and Durability

Bunker, Ronald S.

doi:10.2514/1.11818

Cited by 209 publications

(77 citation statements)

References 10 publications

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“…This results in excessively high metal temperatures on the blade tip, which lead to thermal erosion and oxidation. The loss of the blade tip material increases the tip clearance gap, which reduces the efficiency and work output of the turbine [1]. Therefore, obtaining good thermal performance of the blade tip is the key to maintain the performance of the gas turbine.…”

Section: Introductionmentioning

confidence: 99%

Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

Zhou

2015

International Journal of Heat and Mass Transfer

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Section: Introductionmentioning

confidence: 99%

Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

Zhou

2015

International Journal of Heat and Mass Transfer

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“…A summary of the complex loading and film cooling region associated with the blade tip is provided by Bunker (2006). A recent comprehensive compilation of the art and science of film cooling is contained in the von Karman Institute lecture series of Bunker et al (2007).…”

Section: Film Coolingmentioning

confidence: 99%

Gas Turbine Engines: Turbine Cooling

Bunker

2010

Encyclopedia of Aerospace Engineering

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The advancement of gas turbine cooling has allowed engine design to greatly exceed normal material temperature limits. Cooled component design and development has consistently trended in the direction of higher heat loads, and higher through‐wall and in‐plane thermal gradients. The ultimate goals in gas turbine cooling are consistent with the thermodynamics of isentropic energy transfer in that (1) the component or some portion of it is desired to be isothermal to eliminate all internal thermal stresses, (2) the component is desired to be as hot as allowable to minimize coolant usage and inefficient energy transfers, and (3) thermal gradients from the component to the support and containment structure are desired to be minimized. In terms of the turbine system, the goal of turbine cooling is to achieve the longest component life with the least impact on engine efficiency and cost. This summary describes the means and methods, as well as the constraints, concerning the cooling of gas turbine components.

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“…Sjolander [1] presented an overview of the tip leakage flow, summarized its effect on the performance of axial turbines, and gave an overview of the investigations on the overtip leakage flows. Later, Bunker [2] presented an extensive research review, mainly performed in low-speed environments, on the turbine blade tip aerothermal performance in a high-pressure environment. 7 Having understood the general physics of tip leakage flows, several tip design approaches have been proposed to mitigate tip leakage effects [3] and to improve the thermal performance of blade tips [4].…”

Section: Introductionmentioning

confidence: 99%