Hostname: page-component-cd9895bd7-fscjk Total loading time: 0 Render date: 2024-12-22T11:17:01.956Z Has data issue: false hasContentIssue false
  • English
  • Français

Saving costs in design, manufacturing and operation of aero engine parts

Published online by Cambridge University Press:  04 July 2016

J. Broede
J. Broede*
Affiliation:
MTU Aero EnginesMunich, Germany
Get access Rights & Permissions [Opens in a new window]

Abstract

Basic requirements for aero engine parts are to carry loads at high temperatures safely over service periods of 30-40 years. This generally calls for the best and latest materials and for highly sophisticated design and manufacturing procedures.

These requirements are frequently in contrast to the desire to keep costs at affordable levels. This aims at the costs at both the customer’s side as well as the manufacturer’s side. The measures to reduce cost in the design and production phase are various:

• redesign to allow for less complex manufacturing processes

• reassessment of quality characteristics without reduction of overall quality (only those characteristics to be maintained which are really critical)

• acceptance of minor damage in new parts which would be acceptable for repaired parts according to technical standards

• assessment of all steps in the production process with respect to their influence on the final product properties

• more stabilised manufacturing processes which use only a portion of accepted tolerance bands to reduce the subsequent test effort

• change of material.

In the service phase, cost reduction can be achieved by optimum exploitation of part’s life potential. The means are improvement of the lifing concepts where portions of the crack propagation life may be utilised in addition to the traditionally cleared crack initiation life. Accurate records of life consumption can be obtained with modern systems for life usage monitoring.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1053 , November 2001 , pp. 619 - 626
Copyright
Copyright © Royal Aeronautical Society 2001 

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. Blüml, P. and Broede, J. Critical parts’ life extension based on fracture mechanics, RTO Meeting Proceedings 17 on Qualification and Life Extension Schemes for Engine Components, Corfu, 1998.Google Scholar
2. Pfoertner, H. Extension of the usable engine life by modelling and monitoring, RTO Lecture Series 218bis on Ageing Engines, Avionics, Subsystems and Helicopters, Sofia, 2000.Google Scholar
3. JAA Joint Aviation Requirements, JAR 21.91 Classification of Changes in Type Design.Google Scholar
4. JAA Joint Aviation Requirements, JAR 21.97 Major Changes.Google Scholar
5. JAA Joint Aviation Requirements, JAR 21.33 Inspection and Tests.Google Scholar
6. JAA Joint Aviation Requirements, JAR-E - Engines.Google Scholar
7. Broede, J. Engine life consumption monitoring program tor RB199 integrated in the on-board life monitoring system, AGARD CPP 448, Quebec, 1988.Google Scholar
8. Broede, J. Design and service experience of engine life usage monitoring systems, 5th European Propulsion Forum, Pisa, 1995.Google Scholar
9. Broede, J. and Pfoertner, H. Olmos in GAF MRCA Tornado - 10 years of experience with on-board life usage monitoring, 33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Seattle, 1997.Google Scholar