Hostname: page-component-cd9895bd7-dzt6s Total loading time: 0 Render date: 2024-12-22T10:35:41.407Z Has data issue: false hasContentIssue false
  • English
  • Français

Multidisciplinary methodology for turbine overspeed analysis

Published online by Cambridge University Press:  15 November 2018

I. Eryilmaz ,
L. Pawsey  and
V. Pachidis
I. Eryilmaz
Affiliation:
Centre for Propulsion Engineering, School of Aerospace, Transport and ManufacturingCranfield UniversityBedfordUK
L. Pawsey
Affiliation:
Centre for Propulsion Engineering, School of Aerospace, Transport and ManufacturingCranfield UniversityBedfordUK
V. Pachidis*
Affiliation:
Centre for Propulsion Engineering, School of Aerospace, Transport and ManufacturingCranfield UniversityBedfordUK
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

In this paper, an integrated approach to turbine overspeed analysis is presented, taking into account the secondary air system dynamics and mechanical friction in a turbine assembly following an unlocated high-pressure shaft failure. The axial load acting on the rotating turbine assembly is a governing parameter in terms of overspeed protection since it governs the level of mechanical friction which acts against the turbine acceleration due to gas torque. The axial load is dependent on both the force coming from secondary air system cavities surrounding the disc and the force on the rotor blades. It is highly affected by secondary air system dynamics because rotor movement modifies the geometry of seals and flow paths within the network. As a result, the primary parameters of interest in this study are the axial load on the turbine rotor, the friction torque between rotating and static structures and the axial position of the rotor.

Following an initial review of potential damage scenarios, several cases are run to establish the effect of each damage scenario and variable parameter within the model, with comparisons being made to a baseline case in which no interactions are modelled. This allows important aspects of the secondary air system to be identified in terms of overspeed prevention, as well as guidelines on design changes in current and future networks that will be beneficial for overspeed prevention.

Keywords

Turbine overspeedShaft failureFrictionSecondary air system
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1257 , November 2018 , pp. 1711 - 1733
Copyright
© Royal Aeronautical Society 2018 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. TSBC, Engine Power Loss Canadian North Boeing 737-217 C-GKCP Saskatoon Saskatchewan, Transport Safety Board of Canada, Aviation Investigation Report No. A08C0108, Canada, 2008.Google Scholar
2. NTSB, Safety Recommendation A-06-060, National Transportation Safety Board, USA, 2006.Google Scholar
3. Mons, M. C. Method and Device for Reducing the Speed in the Event of Breakage of a Gas Turbine Engine Turbine Shaft, US Patent No. 20080178603 A1, United States, 2008.Google Scholar
4. ATSB, Uncontained Engine Starter Failure General Electric CF6-80E1-A3 Darwin Aerodrome VH-QPE Airbus A330-300, Australian Transport Safety Bureau, Aviation Occurrence Investigation No. AO-2007-052, Australia, 2008.Google Scholar
5. Gonzalez, A. and Pachidis, V. On the numerical simulation of turbine blade tangling after a shaft failure, ASME Turbo Expo Turbine Conference, GT2014-27061, Germany, 2014, doi:10.1115/GT2014-27061.Google Scholar
6. Haake, M. , Fiola, R. and Staudacher, S. Multistage compressor and turbine modelling for the prediction of the maximum turbine speed resulting from shaft breakage, ASME Turbo Expo Turbine Conference GT2009-59049, USA, 2009, doi:10.1115/1.4001188.Google Scholar
7. Muller, Y. Integrated Fluid Network-Thermomechanical Approach for the Coupled Analysis of a Jet Engine, ASME Turbo Expo Turbine Conference GT2009-59104, USA, 2009, doi:10.1115/GT2009-59104.Google Scholar
8. Muller, Y. Secondary Air System Model for Integrated Thermomechanical Analysis of a Jet Engine, ASME Turbo Expo Turbine Conference GT2008-50078, Germany, 2008, doi:10.1115/GT2008-50078.Google Scholar
9. Ganine, V. , Javiya, N. , Hills, N. and Chew, J. Coupled fluid-structure transient thermal analysis of a gas turbine internal air system with multiple cavities, J of Engineering for Gas Turbines and Power, 2012, 134, (10), 102508. Google Scholar
10. EASA, Certification specifications and Acceptable Means of Compliance for Engines CS-E Amendment 4, European Aviation Safety Agency, 2015.Google Scholar
11. Gallar, L. , Calcagni, C. , Pachidis, V. and Pilidis, P. Development of a one dimensional Dynamic Gas Turbine Secondary Air System Model – Part I: Tool Components Development and Validation, ASME Turbo Expo Turbine Conference GT2009-60058, USA, 2009, doi:10.1115/GT2009-60058.Google Scholar
12. Gallar, L. , Calcagni, C. and Pachidis, V. Development of a One Dimensional Dynamic Gas Turbine Secondary Air System Model – Part II: Assembly and Validation of a Complete Network, ASME Turbo Expo turbine Conference GT2009-60051, USA, 2009, doi:10.1115/GT2009-60051.Google Scholar
13. Mishra, S. General analysis of interdependency of friction factor of a circular pipe with Reynolds number of the flowing fluid & relative roughness parameter of the pipe material, Int J for Technological Research in Engineering, 2016, 3, (7). ISSN (Online): 2347 - 4718 Google Scholar
14. Carslaw, H. and Jaeger, J. Conduction of Heat in Solids, 2nd ed, Chapter 11, Oxford University Press, Great Britain, 1959, pp 292–293.Google Scholar
15. Gonzalez, A. Gas turbine shaft over-speed / failure modelling. Friction and wear modelling of turbines in contact, PhD Thesis,, Cranfield University, Bedford, 2014.Google Scholar
16. Barber, J. Distribution of heat between sliding surfaces, J Mechanical Engineering Science, 1967, 9, (5), pp 351–354.Google Scholar
17. Lefebvre, G. and Durocher, E. Turbine section architecture for gas turbine engine, 2014, US Patent 8734085 B2.Google Scholar
18. Soupizon, J. Device for limiting turbine overspeed in a turbomachine, 2006, US Patent 20060251506 A1.Google Scholar
19. Saravanamuttoo, H. , Rogers, G. and Cohen, H. , Gas Turbine Theory, 5th ed, Chapters 5–7, Pearson Prentice Hall, England, 2001.Google Scholar
20. Pawsey, L. , Rajendran, D. J. and Pachidis, V. Characterisation of turbine behaviour for an engine overspeed prediction model, Aerospace Science and Technology, 2018, 73, (2) pp 10–18.Google Scholar
21. Pawsey, L. , Rajendran, D. J. and Pachidis, V. Aerodynamic Performance of an Unlocated High Pressure Turbine Rotor With Worn Tip Seal Fins, ASME Turbo Expo Turbine Conference. GT2017-64308, USA, 2017.Google Scholar
22. Pawsey, L. , Rajendran, D. J. and Pachidis, V. , Aerodynamic performance of an un-located high-pressure turbine rotor, Aeronaut J, 121, (1242), ISABE 2017 Conference Special Issue, August 2017, pp 1200–1215.Google Scholar
23. Gallar, L. Gas turbine shaft over-speed / failure performance modelling. Aero/Thermodynaimcs Modelling and Overall Engine System Response, PhD Thesis, Cranfield University, Bedford, 2010.Google Scholar