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Research Papers

The Map Fitting Tool Methodology: Gas Turbine Compressor Off-Design Performance Modeling

[+] Author and Article Information
Vishal Sethi

Group Leader, TERA for Civil Aviation
e-mail: v.sethi@cranfield.ac.uk

Georgios Doulgeris

Research Fellow

Pericles Pilidis

Professor and Head of Department

Alex Nind

Ph.D. Researcher
Department of Power and Propulsion,
School of Engineering,
Cranfield University,
Cranfield, MK430AL, UK

Marc Doussinault

Research Program Coordinator
Snecma,
77550 Moissy Cramayel, France

Pedro Cobas

Head of EcosimPro and PROOSIS
Software Development

Almudena Rueda

PROOSIS Software Developer
EA Internacional,
C/ Magallanes, 1,
Madrid 28015, Spain

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 11, 2011; final manuscript received January 31, 2013; published online September 13, 2013. Assoc. Editor: Aspi Wadia.

J. Turbomach 135(6), 061010 (Sep 13, 2013) (15 pages) Paper No: TURBO-11-1077; doi: 10.1115/1.4023903 History: Received May 11, 2011; Revised January 31, 2013

This paper describes the structure and the implementation of an extended parametric representation of compressor characteristics for a modern object oriented gas turbine performance simulation software (PROOSIS). The proposed methodology is the map fitting tool (MFT) methodology. The proposed MFT methodology for modeling the off design performance of gas turbine turbomachinery components (fans, compressors, and turbines) is based on a concept conceived and developed collaboratively by General Electric (GE) and NASA. This paper provides a short description of both BETA and MFT compressor maps, as well as the development of compressor component models in PROOSIS capable of using both types of maps for off design compressor performance prediction. The work presented in this paper is the outcome of a collaborative effort between Snecma Moteurs and Cranfield University as part of the European Cycle Program of the EU FP6 collaborative project—VIVACE. A detailed description of the MFT map methodology is provided with a “step-by-step” calculation procedure. Synergies between compressor MFT and compressor BETA calculations are also highlighted and a description of how these two components have been integrated into an object oriented simulation software with component hierarchy is also presented. Advanced parametric representations of fan and turbine characteristics have also been developed within PROOSIS. However, a description of these methodologies is beyond the scope of this publication. Additionally, a comparison between the advantages and disadvantages between BETA and MFT maps is an interesting debate. However, this is also beyond the scope of this paper.

Copyright © 2013 by ASME
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References

Figures

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Fig. 1

Structure of the VIVACE project [1,2]

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Fig. 2

Screenshot of the PROOSIS modeling environment showing the engine schematic canvas

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Fig. 3

“TURBO” component hierarchy (abstract level)

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Fig. 4

Compressor MFT component hierarchy

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Fig. 5

A typical compressor BETA line map

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Fig. 6

Compressor ghr versus gl characteristic

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Fig. 7

Compressor MFT map choke limits

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Fig. 8

Visualization of a typical compressor MFT map [19]

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Fig. 9

Sample “ghchoke_versus_NCRdes” characteristic

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Fig. 10

Sample “ghml_versus_NcRdes” characteristic

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Fig. 11

Effects of s_gh on a typical compressor MFT map [19]

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Fig. 12

Sample “glml_versus_NcRdes” characteristic

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Fig. 13

Sample of “gld_versus_gh_NcRdes” characteristic

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Fig. 14

PROOSIS test analysis process [24]

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Fig. 15

Sample “VqU_versus_NcRdes” characteristic

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Fig. 16

Sample “MNj_versus_gh_NcRdes” characteristic

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