Contribution of Heat Transfer to Turbine Blades and Vanes for High Temperature Industrial Gas Turbines Part 1: Film Cooling

Takeishi, Kenichiro; Aoki, S.

doi:10.1111/j.1749-6632.2001.tb05864.x

Cited by 13 publications

(8 citation statements)

References 3 publications

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“…Research related to the enhancement of TIT has been pivotal for achieving higher thermal efficiencies. [1][2][3] First stage rotating blades of high-pressure turbines are the most sensitive components of the gas turbine engine owing to their exposure to harsh TITs coupled with dynamic loads due to rotation of blades. Superalloys of nickel, cobalt, and iron-nickel used as blade materials retain their mechanical properties at such harsh conditions.…”

Section: Introductionmentioning

confidence: 99%

Thermodynamics of CMC bladed marine gas turbine-LM 2500: Effect of cycle operating parameters

Rathore

Kar

Sanjay

2022

International Journal of Engine Research

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Recent developments in ceramic-matrix composites and their successful use in combustor liners and shrouds have generated interest among researchers to adopt these materials in rotating gas turbine blades, especially in the first stages of high-pressure turbines where gas temperatures are highest. CMC blades have the potential of being retrofitted to replace superalloy turbine blades in operating gas turbines. In this paper, a comparative study on the thermodynamic performance of a marine gas turbine engine, LM 2500, featuring directionally solidified nickel superalloy blades versus novel CMC blades in the high-pressure turbine sections has been reported. Mathematical modeling of the gas turbine cycle components has been developed and then coded in C++ language. The effects of turbine inlet temperature on thermodynamic efficiencies, coolant mass flow rates, and work ratios on the two systems have been analyzed. Finally, the exergy analysis of the systems’ components has been done to identify the benefits of adopting CMC blades in the LM 2500 system. It has been observed that when compared to the directionally solidified bladed turbine system, the projected first law efficiency of CMC bladed LM 2500 gas turbines can be enhanced over 7% (from 34.17% to 41.21%). The projected work ratio can be improved by over 16% (from 0.49 to 0.57) at the turbine inlet temperature of 1725 K.

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Section: Introductionmentioning

confidence: 99%

Thermodynamics of CMC bladed marine gas turbine-LM 2500: Effect of cycle operating parameters

Rathore

Kar

Sanjay

2022

International Journal of Engine Research

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“…A schematic view of the wind tunnel is shown in Figure 1. Figure 2 shows the geometry of film cooling holes, whose shapes are similar shapes to those used by Takeishi and Aoki [7]. They were made of low thermal conductivity material (Sanyo-chemical SanmodurMS) to reinforce the adiabatic condition.…”

Section: Wind Tunnel and Film Cooling Modelsmentioning

confidence: 99%

“…Efforts to improve film cooling efficiency by adopting film cooling holes with expanded exits have been made experimentally by Goldstein and Eckert [5], Bell et al [6], Takeishi and Aoki. [7] and Yu et al [8]. An excellent summary paper on shaped film cooling was published by Bunker [9].…”

Section: Introductionmentioning

confidence: 99%

Film cooling with swirling coolant flow

Takeishi¹,

Oda²,

Egawa³

et al. 2010

Advanced Computational Methods and Experiments in Heat Transfer XI

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This paper describes the experimental results of a new film cooling method blowing through circular and shaped film cooling holes with swirling coolant flow. The experiments have been conducted by using a low-speed wind tunnel. The film cooling effectiveness on the flat wall was measured by using pressure sensitive paint (PSP) techniques. In addition, the spatial distribution of the film cooling effectiveness and flow field were measured by leaser induced fluorescence (LIF) and particle image velocimetry (PIV), respectively. In the case of the circular film cooling hole, the coolant jet penetration into the mainstream is suppressed by the swirling motion of the coolant. As a result, although the coolant jet is deflected in the pitch direction, the film cooling effectiveness distribution on the wall keeps a higher value behind the cooling hole over a long range. Additionally, the anti-kidney vortex structure disappeared. For the shaped cooling hole, the coolant jet spreads wider in the spanwise direction at the downstream. Thus, the pitch averaged film cooling effectiveness at the downstream was 50% higher than that of the non-swirling case.

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“…The efforts to improve film cooling efficiency by adopting film cooling holes with expanded exits have been made experimentally by Goldstein and Eckert [5], Bell et al [6], Takeishi and Aoki. [7] and Yu et al [8]. Excellent summary paper on shaped film cooling was published by B nker [9].…”

Section: Introductionmentioning

confidence: 99%

An experimental study of a film cooling with swirling flow on the endwall of a high loaded 1st nozzle

Takeishi¹,

Oda²,

Kondo³

2012

Advanced Computational Methods and Experiments in Heat Transfer XII

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This paper describes an experimental study on film cooling effectiveness of circular and fan-shaped film cooling holes with a swirling film coolant injected through the endwall of a high-loaded 1st nozzle. The experiments have been conducted by using a two dimensional vane cascade, designed based on the firststage vane of E 3 (Energy Efficient Engine) engine studied by a NASA project. The film cooling effectiveness on the endwall of the enlarged 1st nozzle of E 3 turbine was measured by using pressure sensitive paint (PSP) techniques. It appeared from the experimental results that the film cooling effectiveness of a circular hole was improved by increasing the angle of two impingement jets inside the cavity, which is used both to cool internal wall and to produce a swirling motion of film coolant. On the other hand, it was found that there exists an optimal jet angle between  to 15 degrees in the case of a fan shaped film cooling hole. Thus the new film cooling method with swirling cooling air has been demonstrated to maintain its high film cooling effectiveness even under such a complicated flow field.

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Contribution of Heat Transfer to Turbine Blades and Vanes for High Temperature Industrial Gas Turbines Part 1: Film Cooling

Cited by 13 publications

References 3 publications

Thermodynamics of CMC bladed marine gas turbine-LM 2500: Effect of cycle operating parameters

Thermodynamics of CMC bladed marine gas turbine-LM 2500: Effect of cycle operating parameters

Film cooling with swirling coolant flow

An experimental study of a film cooling with swirling flow on the endwall of a high loaded 1st nozzle

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