Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1 — Experimental Technique and Results

Harasgama, S. P.; Burton, Christy

doi:10.1115/91-gt-252

Cited by 13 publications

(4 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In recent years, there have been many studies in turbine blade film cooling. For example, Abhari and Epstein (1994) studied rotor blade film cooling, Nirmalan and Hylton (1990) reported on linear cascade nozzle guide vane film cooling, Camci and Arts (1985) studied the linear cascade blade film cooling, Harasgama and Burton (1992) presented annual cascade nozzle guide vane end-wall film cooling, Mehendale and Han (1992) studied the modeled blade leading edge film cooling, and Kim et al (1995) reported on the modeled blade tip film cooling. A detailed literature survey in film cooling study can be found in Han and Ekkad (2001), Han et al (2000), and Dunn (2001).…”

Section: Recent Studies On Turbine Blade Film Coolingmentioning

confidence: 99%

Recent Studies in Turbine Blade Cooling?

Han¹

2004

The International Journal of Rotating Machinery

View full text Add to dashboard Cite

Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. Developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbines. Gas turbine blades are cooled internally by passing the coolant through several rib-enhanced serpentine passages to remove heat conducted from the outside surface. External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form a protective layer between the blade surface and hot gas-path flow. For internal cooling, this presentation focuses on the effect of rotation on rotor blade coolant passage heat transfer with rib turbulators and impinging jets. The computational flow and heat transfer results are also presented and compared to experimental data using the RANS method with various turbulence models such as k-ε, and second-moment closure models. This presentation includes unsteady high free-stream turbulence effects on film cooling performance with a discussion of detailed heat transfer coefficient and film-cooling effectiveness distributions for standard and shaped film-hole geometry using the newly developed transient liquid crystal image method.

show abstract

Section: Recent Studies On Turbine Blade Film Coolingmentioning

confidence: 99%

Recent Studies in Turbine Blade Cooling?

Han¹

2004

The International Journal of Rotating Machinery

View full text Add to dashboard Cite

show abstract

“…Coolant ejection locations have to be viewed with respect to the three-dimensional separation lines on the endwall, taking account of the fact that these can be changed due to upstream endwall coolant ejection. Previous investigations of endwall filmcooling, such as the ones by Blair (1974), Takeishi et al (1989), Granser and Schulenberg (1990), Bourguignon (1985), Bario et al (1989), Harasgama and Burton (1991), Jabbari et al (1994), Goldman and McLallin (1977) and Sieverding and Wilputte (1980) support these conclusions.…”

Section: Introductionmentioning

confidence: 60%

The Design of an Improved Endwall Film-Cooling Configuration

Friedrichs

Hodson

Dawes

1998

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

View full text Add to dashboard Cite

The endwall film-cooling cooling configuration investigated by Friedrichs et al. (1996, 1997) had in principle sufficient cooling flow for the endwall, but in practice, the redistribution of this coolant by secondary flows left large endwall areas uncooled. This paper describes the attempt to improve upon this datum cooling configuration by redistributing the available coolant to provide a better coolant coverage on the endwall surface, whilst keeping the associated aerodynamic losses small. The design of the new, improved cooling configuration was based on the understanding of endwall film-cooling described by Friedrichs et al. (1996, 1997). Computational fluid dynamics were used to predict the basic flow and pressure field without coolant ejection. Using this as a basis, the above described understanding was used to place cooling holes so that they would provide the necessary cooling coverage at minimal aerodynamic penalty. The simple analytical modelling developed in Friedrichs et al. (1997) was then used to check that the coolant consumption and the increase in aerodynamic loss lay within the limits of the design goal. The improved cooling configuration was tested experimentally in a large scale, low speed linear cascade. An analysis of the results shows that the redesign of the cooling configuration has been successful in achieving an improved coolant coverage with lower aerodynamic losses, whilst using the same amount of coolant as in the datum cooling configuration. The improved cooling configuration has reconfirmed conclusions from Friedrichs et al. (1996, 1997); firstly, coolant ejection downstream of the three-dimensional separation lines on the endwall does not change the secondary flow structures; secondly, placement of holes in regions of high static pressure helps reduce the aerodynamic penalties of platform coolant ejection; finally, taking account of secondary flow can improve the design of endwall film-cooling configurations.

show abstract

“…Studies of sectored [9] and annular [10] louvers have facilitated a better justified analysis of the change in the structure of the secondary flows and made it possible to estimate the losses when air is released through the end surfaces. Figure 1b is a graph of the loss coefficient ae as a function of the height of the flow-through part behind the sector packet with ë 2ad.avg = 1.12 without release of cooling air on the end surfaces G air.end = 0 and with release of cooling air through apertures on the end surfaces, G air.end = 0.013.…”

Section: Experimental Study Of the Blade Apparatus Of A Stagementioning

confidence: 99%

Analysis of physical processes and operating behavior of gas turbine units with high loading of the gas turbine stage

Granovskiy

2011

Power Technol Eng

View full text Add to dashboard Cite

Aspects of using a highly loaded stage in place of a group of stages in gas turbines are analyzed. Experimental data for individual wheels, as well as for the entire stage as a whole, are presented which confirm the possibility of obtaining efficiencies relative to braking of 0.87 -0.89 during operation of the stage with turbine load parameters of 0.40 -0.48. This makes it possible to reduce the number of stages without significant loss of gas dynamic efficiency. The cooling air feed rate is lowered and fewer parts are needed, thereby reducing the cost of the entire turbine.

show abstract

Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1 — Experimental Technique and Results

Cited by 13 publications

References 1 publication

Recent Studies in Turbine Blade Cooling?

Recent Studies in Turbine Blade Cooling?

The Design of an Improved Endwall Film-Cooling Configuration

Analysis of physical processes and operating behavior of gas turbine units with high loading of the gas turbine stage

Contact Info

Product

Resources

About