Material shortages - Effect on the aircraft engine industry

1981 ◽  
Author(s):  
M. SIEGEL
Keyword(s):  
Aircraft Engine ◽  
Engine Industry

ALGORITHM FOR CALCULATING THE SURFACE ROUGHNESS PARAMETERS OF A PART MADE USING ADDITIVE TECHNOLOGY

2021 ◽  
pp. 12-15
Author(s):  
V. F. Bezyazychnyj ◽  
D. V. Fedoseev
Keyword(s):  
Surface Roughness ◽  
Aircraft Engine ◽  
Laser Fusion ◽  
Roughness Parameters ◽  
Additive Technology ◽  
Calculation Algorithm ◽  
Surface Roughness Parameters ◽  
Engine Industry ◽  
Selective Laser Fusion

The calculated dependences for determining the surface roughness parameters of a part made by selective laser fusion from materials that are certified and widely used in the aircraft engine industry are presented. A comparison of the values of the height parameters of the roughness obtained by calculation and on the basis of the experiment is presented. On the basis of the presented dependencies, a calculation algorithm is developed, which is the basis of the software for calculating on a computer.

scholarly journals A Rational Determination of Permitted Usable Lives for Gas Turbine Engine Components

1970 ◽  
Author(s):  
T. L. Salt
Keyword(s):  
Crack Initiation ◽  
Gas Turbine ◽  
Aircraft Engine ◽  
Rational Approach ◽  
Engine Operation ◽  
Turbine Engine ◽  
First Case ◽  
Engine Industry ◽  
The Many

The specification of permitted usable lives, or as they are frequently called “life limits,” is an F.A.A. requirement for critical aviation gas turbine rotating components in commercial use (1). To establish these life limits in a consistent conservative manner, a statistical analysis is necessary to assimilate the many variables involved. The most important parameters are the expected component deterioration with use, the characteristics of this use and the chosen overhaul times and maintenance procedures. Considerable effort has been expended in the aircraft engine industry to obtain better recordings of actual engine operation and environment. A paper by Hohenburg (2) which was principally concerned with such monitoring devices did, however, state “Users of engines must make decisions on when to perform maintenance, to overhaul, or to retire engines from service …. There is a substantial requirement for rational determination of maintenance and retirement intervals.” This paper demonstrates such a rational approach in the form of computer program SMILE (Statistical, Maintenance, Inspection and Life Evaluation). It compares, on the basis of estimated risk, alternative choices of life limits by including all the principal parameters involved. An example makes a comparison of a component with early crack initiation and substantial propagation before failure with an alternative design having late crack initiation but virtually infinitely fast propagation. It shows how a life limit may be considered redundant but necessary in the first case and essential in the second. The alternative risks with specified permitted usable lives will be estimated for each design.

Platform Strategies for a Supplier in the Aircraft Engine Industry

2008 ◽  
Author(s):  
Fredrik Berglund ◽  
Dag Bergsjo¨ ◽  
Ulf Ho¨gman ◽  
Kiran Khadke
Keyword(s):  
Automotive Industry ◽  
Focal Point ◽  
Aircraft Engine ◽  
Product Line ◽  
Production Environment ◽  
Core Technology ◽  
Engine Industry ◽  
Platform Development ◽  
Development Literature ◽  
Competitive Priority

The utilization of a platform strategy has become a competitive priority in many industries, most notably in the automotive industry. Naturally, many firms in other industries are adopting this strategy with different modifications and degrees of implementation. However, little research covers the application of platform development in a supplier and/or small batch production environment. The adaptation of a platform strategy in these settings, by a supplier in the aircraft engine industry, is the focal point of this paper. Based on platform development literature and the characteristics of the aircraft engine industry and the company studied advantages and hindrances for platform strategies have been ruled out. Interviews with involved people within the company studied have further clarified different perspectives on platforms and their possible utilization. Based on the analysis of collected information it is proposed that a possible platform strategy would include: a technology platform, incorporating general knowledge on core technology assets embodied in either humans, organizations, processes, information or methods; and a product platform, incorporating product specific elements that could be re-used when developing new components for a particular product line.

Prospective Magnesium Alloys with Elevated Level of Properties for the Aircraft Engine Industry

2014 ◽  
Vol 55 (9-10) ◽  
pp. 492-498 ◽  
Author(s):  
V. I. Velikiy ◽  
K. I. Yares’ko ◽  
V. A. Shalomeev ◽  
E. I. Tsivirko ◽  
Yu. N. Vnukov
Keyword(s):  
Magnesium Alloys ◽  
Elevated Level ◽  
Aircraft Engine ◽  
Engine Industry

Aircraft Engine Developments During the Past Half Century

1966 ◽  
Vol 70 (661) ◽  
pp. 150-167
Author(s):  
Frank Nixon
Keyword(s):  
Great Majority ◽  
Aircraft Engine ◽  
Source Material ◽  
Half Century ◽  
The Past ◽  
Past Half Century ◽  
Engine Industry ◽  
Team Spirit ◽  
Past Half

As was said of Richard Trevithick, “Practical men are too apt to leave facts unrecorded”, and this is particularly true of those involved in the development of Britain's aircraft engine industry.The names of a few people come to mind immediately, but there are others whose contribution has played a crucial yet barely-recognised part in directing the overall trend. In addition there are many others who have filled lesser but vital roles as members of the teams led by the better-known pioneers.Source-material on which to base an account of the work of Society members is scanty, since the great majority of published papers have preserved that strict anonymity which is indicative of British “team spirit”.

High-Temperature Instability of A Cr2Nb-Nb(Cr) Microlaminate Composite

1996 ◽  
Vol 54 ◽  
pp. 374-375
Author(s):  
M. Larsen ◽  
R.G. Rowe ◽  
D.W. Skelly
Keyword(s):  
Heat Treatment ◽  
Solid Solution ◽  
High Temperature ◽  
Elevated Temperatures ◽  
Aircraft Engine ◽  
Lattice Parameter ◽  
Microstructural Stability ◽  
Elevated Temperature Strength ◽  
Cross Sectional ◽  
Bcc Structure

Microlaminate composites consisting of alternating layers of a high temperature intermetallic compound for elevated temperature strength and a ductile refractory metal for toughening may have uses in aircraft engine turbines. Microstructural stability at elevated temperatures is a crucial requirement for these composites. A microlaminate composite consisting of alternating layers of Cr2Nb and Nb(Cr) was produced by vapor phase deposition. The stability of the layers at elevated temperatures was investigated by cross-sectional TEM.The as-deposited composite consists of layers of a Nb(Cr) solid solution with a composition in atomic percent of 91% Nb and 9% Cr. It has a bcc structure with highly elongated grains. Alternating with this Nb(Cr) layer is the Cr2Nb layer. However, this layer has deposited as a fine grain Cr(Nb) solid solution with a metastable bcc structure and a lattice parameter about half way between that of pure Nb and pure Cr. The atomic composition of this layer is 60% Cr and 40% Nb. The interface between the layers in the as-deposited condition appears very flat (figure 1). After a two hour, 1200 °C heat treatment, the metastable Cr(Nb) layer transforms to the Cr2Nb phase with the C15 cubic structure. Grain coarsening occurs in the Nb(Cr) layer and the interface between the layers roughen. The roughening of the interface is a prelude to an instability of the interface at higher heat treatment temperatures with perturbations of the Cr2Nb grains penetrating into the Nb(Cr) layer.

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