Application and Improvement of Gas Turbine Blades Film Cooling

Koval, S.

doi:10.1007/978-981-13-6061-9_5

Cited by 3 publications

(2 citation statements)

References 19 publications

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“…This method is known as film cooling and can achieve a difference of a few hundred degrees between the gases and wall temperature. The injection mechanism in a film cooling system has been the main topic for a number of works, such as [4][5][6][7][8][9][10][11], studying the influence of different parameters on the film flow and its effectiveness. The main difference between the film cooling injection and the system proposed in [2,3] is that, in the case of cooling, the objective of injection is to create a layer on the surface of the vane or blade without disturbing the flow through the turbine.…”

Section: Introductionmentioning

confidence: 99%

Application of a Performance-Improvement Method for Small-Size Axial Flow Turbines

Nicoara,

Crunteanu,

Vilag

2023

Aerospace

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As a main component of most gas-turbine engines, the axial flow turbines have been in a process of continuous improvement, reaching high efficiencies and reliability. A well-known drawback of these systems is the rapid decrease in performance when operating at lower than nominal conditions. Thus, a novel performance-enhancement method for axial turbines operating at partial loads has been previously proposed and numerically characterized. In this paper, one applies the aforementioned method for a smaller size axial flow turbine, part of a gas-generator assembly for a microjet engine, to determine, by the use of CFD analysis, the influence of the system at different partial regimes across the working line. A logical scheme based on iterative steps and multiple numerical simulations is also used to determine the engine response to the injection of compressor bleed air into the turbine passages. The results show, as determined in the previous study, that the generated power can be increased for all partial regimes, with the influence being more noticeable at higher regimes, leading to a reduction in fuel consumption in order to achieve the same regimes.

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Section: Introductionmentioning

confidence: 99%

Application of a Performance-Improvement Method for Small-Size Axial Flow Turbines

Nicoara,

Crunteanu,

Vilag

2023

Aerospace

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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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Thermodynamic Analysis of Aeroderivative Gas Turbine Engine Featuring Ceramic Matrix Composite Rotating Blades

Rathore

Kar

Sanjay

et al. 2021

SAE Technical Paper Series

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Application and Improvement of Gas Turbine Blades Film Cooling

Cited by 3 publications

References 19 publications

Application of a Performance-Improvement Method for Small-Size Axial Flow Turbines

Application of a Performance-Improvement Method for Small-Size Axial Flow Turbines

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

Thermodynamic Analysis of Aeroderivative Gas Turbine Engine Featuring Ceramic Matrix Composite Rotating Blades

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