A Brief History of Aircraft Engine Development at General Electric

Purpose The purpose of this study is to improve life prediction of certain components. Fatigue of the high-stressed structural elements is an essential parameter that affects the lifetime of such components. In particular, aviation engines are devices whose failure due to fatigue failure of one of the important components can lead to fatal consequences. Design/methodology/approach In this study, two analyses in the turbine disk of the jet engine during the simulated operating load were performed: The first one was the analysis of the heat-induced stresses using the finite element method. The goal of the second analysis was to determine the residual fatigue strength of a loaded disk by the software tool using the Palmgren - Miner Linear Damage Theory. Findings The results showed a high degree of similarity with the real tests performed on the aircraft engine and revealed the weak points in the design of the jet engine. Research limitations/implications It should be mentioned that without appropriate experiments, results of this analysis could not be verified. Practical implications These results are helpful in the re-designing of the jet engines to increase their technical feasibility. Originality/value Such analysis has been realized in the DV-2 jet engine research and development program for the first time in the history of jet engine manufacturing process in Slovakia and countries of Eastern Europe region.

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Design and Development Review of the T64 Turboprop/Turboshaft Engine

ASME 1961 Gas Turbine Power Conference and Exhibit ◽

10.1115/61-gtp-7 ◽

1961 ◽

Author(s):

Frederic F. Ehrich

Keyword(s):

Aircraft Engine ◽

Design Criteria ◽

Basic Design ◽

Design And Development ◽

Development Review ◽

Development Experience ◽

Turboshaft Engine ◽

Engine Development ◽

Small Aircraft

The T64 is a turboshaft/turboprop aircraft engine under development by the Small Aircraft Engine Department of the author’s company for the U. S. Navy Bureau of Weapons. A summary is given of the basic design criteria for the engine as well as a brief description of the engine configuration and highlights of engine development experience. A summary of the engine configuration is given in Table 1.

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A Fluid-Structure Case Study in Simulation Lifecycle Management

Volume 3: Advanced Composite Materials and Processing; Robotics; Information Management and PLM; Design Engineering ◽

10.1115/esda2012-82935 ◽

2012 ◽

Author(s):

Yannick Kibamba ◽

William Derigent ◽

Benoît Eynard

Keyword(s):

Aircraft Engine ◽

Fluid Structure ◽

Compressor Design ◽

Lifecycle Management ◽

Engine Development

This paper aims at presenting an approach to structuring interactions within product, through a graph, for simulation purposes. This approach has been developed for specific needs on Simulation Lifecycle Management (SLM) dedicated to aircraft engine development. The paper also illustrates the implementation of this approach on a case study which concerns a compressor design.

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The Science, Technology, and Implementation of TiAl Alloys in Commercial Aircraft Engines

MRS Proceedings ◽

10.1557/opl.2013.44 ◽

2013 ◽

Vol 1516 ◽

pp. 49-58 ◽

Cited By ~ 85

Author(s):

B. P. Bewlay ◽

M. Weimer ◽

T. Kelly ◽

A. Suzuki ◽

P.R. Subramanian

Keyword(s):

Titanium Aluminide ◽

Turbine Blades ◽

Aircraft Engine ◽

Low Pressure ◽

Major Advance ◽

Commercial Aircraft ◽

Tial Alloys ◽

Low Pressure Turbine ◽

Titanium Aluminide Alloy ◽

History Of

ABSTRACTThe present article will describe the science and technology of titanium aluminide (TiAl) alloys and the engineering development of TiAl for commercial aircraft engine applications. The GEnxTM engine is the first commercial aircraft engine that is flying titanium aluminide (alloy 4822) blades and it represents a major advance in propulsion efficiency, realizing a 20% reduction in fuel consumption, a 50% reduction in noise, and an 80% reduction in NOx emissions compared with prior engines in its class. The GEnxTM uses the latest materials and design processes to reduce weight, improve performance, and reduce maintenance costs.GE’s TiAl low-pressure turbine blade production status will be discussed along with the history of implementation. In 2006, GE began to explore near net shape casting as an alternative to the initial overstock conventional gravity casting plus machining approach. To date, more than 40,000 TiAl low-pressure turbine blades have been manufactured for the GEnxTM 1B (Boeing 787) and the GEnxTM 2B (Boeing 747-8) applications. The implementation of TiAl in other GE and non-GE engines will also be discussed.

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