Effect of New Blade Cooling System With Minimized Gas Temperature Dilution on Gas Turbine Performance

Kawaike, Kazuhiko; Kobayashi, Nariyoshi; Ikeguchi, Takashi

doi:10.1115/1.3239635

Cited by 18 publications

(9 citation statements)

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“…The cooled stage model adopted in this study is depicted in Fig.l, where temperature and pressure losses are treated separately. The model is basically similar to the previous ones(Louis et al, 1983, El-Masri, 1988. The stage efficiency during work extraction(2-3) may be interpreted as the uncooled efficiency.…”

Section: Gas Turbine Modelingsupporting

confidence: 72%

“…However, the evolution of gas turbine performance and configuration has urged the system analysts to develope more efficient and precise performance evaluation programs. Up to now, several efforts have been made to analyze the gas turbine systems and several unique and characteristic models for the gas turbine components have been introduced, specially focusing on the cooled turbine prediction (Louis et al, 1983, El-Masri, 1988, Erbes et al, 1989, Consonni et al, 1991. Only the thermal performance prediction is the primary objective in many studies.…”

Section: Introductionmentioning

confidence: 99%

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Comparative Evaluation of the Effect of Turbine Configuration on the Performance of Heavy-Duty Gas Turbines

Kim

1995

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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Performance of the heavy-duty gas turbine is analyzed with a special focus on the effect of turbine configuration. A general program is developed to fully represent the real component features by the characteristic models. The program is applied to simulate the performance of current heavy-duty gas turbines and its appropriateness for system analysis is verified. Meanwhile, the component parameters of real engines which describe the technology level are obtained. The effect of turbine parameters on the overall gas turbine performance is comparatively evaluated. A special emphasis is put on the analysis of the effect of number of turbine stages on the gas turbine performance and maximum power. Definite performance discrepancy due to the difference in the number of turbine stages is presented. It is found that number of turbine stages considerably affects the maximum gas flow and thermodynamic performance enhancement of the high-temperature advanced gas turbine is meaningful only when the mechanical constraint is relaxed.

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Section: Gas Turbine Modelingsupporting

confidence: 72%

Section: Introductionmentioning

confidence: 99%

Comparative Evaluation of the Effect of Turbine Configuration on the Performance of Heavy-Duty Gas Turbines

Kim

1995

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…total pressure P mass averaged total pressure, see equation 12• static pressure cooling on the overall performance of gas turbine engines (Kawaike et al, 1984, El-Masri, 1986, Kim and Ro, 1995. To predict the performance of an engine, however, there should be a clear understanding of the phenomena in cooled turbines.…”

Section: Nomenclature Amentioning

confidence: 99%

Performance Analysis of a Turbine Stage Having Cooled Nozzle Blades With Trailing Edge Ejection

Kim

Lee

et al. 1996

ASME 1996 Turbo Asia Conference

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This work presents an aerothermodynamic modeling of a cooled turbine blade and the performance analysis of a turbine stage having cooled nozzle blades with trailing edge coolant ejection. A mean line analysis, based on the well-known Ainley-Mathieson scheme, is adopted for the basic loss prediction of the blade rows without cooling. A unique model regarding the interaction between coolant and main gas is proposed. The interactions considered are the heat transfer from main gas to coolant and the temperature and pressure losses by the mixing of two streams due to the trailing edge coolant ejection. For a model turbine stage with nozzle cooling, parametric analyses are carried out to investigate the effect of main design variables (amount of coolant flow, coolant temperature and coolant ejection area) on the stage performance. The influences of coolant mass flow ratio and temperature on the mixing loss and specific work are investigated. The results are also rearranged to investigate the effect of blade temperature on the specific work. Analysis is also carried out by varying the ejection area, which may give useful criteria in determining the coolant condition and ejection hole size of real gas turbine engines.

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“…Once the allowable limit is reached, a larger growth rate is required to not further increase the stress level. In case a constant maximum stress is used for the design, an analytical formulation is of the area increase is possible, such as given by Kawaike [25]. However, using only the stress limit which was obtained from the hottest cross section, would create a very conservative and too heavy a design.…”

Section: F{r) = Poj-[ ' A(r)rdr and A{r) = ç-F ' A{r)rdr (23)mentioning

confidence: 99%

Lifing Requirement Based Turbine Airfoil Mass Estimation Method in Conceptual Aero-Engine Design

Bretschneider

Weisser

Klingels

et al. 2012

Journal of Engineering for Gas Turbines and Power

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For a given material, the target lifetime can be translated into a maximally allowable material temperature and stress level. While the latter has to be maintained by an appropriate mechanical design of the turbine blades, the material temperature needs to be established by sufficient cooling air. The predominant life-limiting effects are taken into account to determine the allowable temperatures and stresses as an accumulation of the varying operating condition over a flight cycle. The applicable stress levels are then used to calculate the necessary radial area distribution of the airfoil and by this a prediction of its mass is possible. Furthermore, the methodology estimates the required amount of cooling air per airfoil cascade from the computed material temperatures. Example calculations are presented and discussed which illustrate design trends and the benefits which are gained from the proposed /úí.The authors want to point out, that the intent of the proposed method is not to deliver an aerodynamic design of the airfoil. The method was developed to enable a more realistic mass estimation Journal of Engineering for Gas Turbines and Power

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Effect of New Blade Cooling System With Minimized Gas Temperature Dilution on Gas Turbine Performance

Cited by 18 publications

References 0 publications

Comparative Evaluation of the Effect of Turbine Configuration on the Performance of Heavy-Duty Gas Turbines

Comparative Evaluation of the Effect of Turbine Configuration on the Performance of Heavy-Duty Gas Turbines

Performance Analysis of a Turbine Stage Having Cooled Nozzle Blades With Trailing Edge Ejection

Lifing Requirement Based Turbine Airfoil Mass Estimation Method in Conceptual Aero-Engine Design

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