Research Papers

A Calculation Tool of a Turbine Cooling Air Schedule for General Gas Turbine Simulation Algorithms

[+] Author and Article Information
Valerio Lallini

Department of Power and Propulsion, Cranfield University, SOE Whittle Building, Cranfield, Bedford MK43 0AL, UKvaleriolallini@hotmail.it

Jan Janikovic

Department of Power and Propulsion, Cranfield University, SOE Whittle Building, Cranfield, Bedford MK43 0AL, UKjanikovic@yahoo.com

Pericles Pilidis, Riti Singh, Panagiotis Laskaridis

 Cranfield University, Cranfield, Bedford MK43 0AL, UK

J. Turbomach 134(4), 041003 (Jul 19, 2011) (8 pages) doi:10.1115/1.4003648 History: Received January 22, 2010; Revised November 24, 2010; Published July 19, 2011; Online July 19, 2011

A tool to evaluate the turbine cooling air schedule during the flight path is presented. The method is suitable for complex gas turbine engine models where accurate calculation of thermodynamic parameters of a cooling flow used for studies such as specific fuel consumption (SFC), lifing, and operating cost analysis. The method is also applicable for land-based gas turbine engines where the flight path is replaced by load pattern. The method can be employed even if only a little information about the engine is known. The calculation method has been investigated on a model of a high bypass ratio turbofan for long haul application. Using it with an aircraft model and after comparing to conventional cooling air simulations, the reduction of SFC during the flight path has been observed. A comparison has been performed on engine manufacturer’s public domain data where the method shows comparable value of total cooling air needed. The tool returns similar results but estimates a higher proportion of cooling air for the high pressure turbine nozzle guide vanes (NGV) compared with Young and Wilcock’s method.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 2

Quasi-1D turbine design procedure

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Figure 3

Cooling flow calculation procedure

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Figure 4

Multistep expansion of the cooled turbine stage

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Figure 5

Turbine blade thermal boundary layer

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Figure 6

Heat transfer process across the cooled turbine blade with TBC

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Figure 7

Comparison between proposed model and data from an industrial source

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Figure 8

Comparison between present method and method from Young and Wilcock

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Figure 9

Cooling mass flow variation along the flight path

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Figure 10

Engine specific fuel consumption for 7 h flight

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Figure 11

Engine specific fuel consumption during the cruise segment

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Figure 12

Percentage of the SFC reduction in the case of scheduled cooling air (constant cooling air is the basic case)

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Figure 1

Engine model layout




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