scholarly journals Key aerodynamic technologies for aircraft engine nacelles

2006 ◽  
Vol 110 (1107) ◽  
pp. 265-288 ◽  
Author(s):  
S. Raghunathan ◽  
E. Benard ◽  
J. K. Watterson ◽  
R. K. Cooper ◽  
R. Curran ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Life Cycle ◽  
Life Cycle Cost ◽  
Aircraft Design ◽  
Aircraft Engine ◽  
Customer Requirements ◽  
Next Generation ◽  
Pressure Relief ◽  
Transport Aircraft ◽  
Conducting Research

AbstractCustomer requirements and vision in aerospace dictate that the next generation of civil transport aircraft should have a strong emphasis on increased safety, reduced environmental impact and reduced cost without sacrificing performance. In this context, the School of Mechanical and Aerospace Engineering at the Queen’s University of Belfast and Bombardier have, in recent years, been conducting research into some of the key aerodynamic technologies for the next generation of aircraft engine nacelles. Investigations have been performed into anti-icing technology, efficient thrust reversal, engine fire zone safety, life cycle cost and integration of the foregoing with other considerations in engine and aircraft design. A unique correlation for heat transfer in an anti-icing system has been developed. The effect of normal vibration on heat transfer in such systems has been found to be negligible. It has been shown that carefully designed natural blockage thrust reversers without a cascade can reduce aircraft weight with only a small sacrifice in the reversed thrust. A good understanding of the pressure relief doors and techniques to improve the performance of such doors have been developed. Trade off studies between aerodynamics, manufacturing and assembly of engine nacelles have shown the potential for a significant reduction in life cycle cost.

scholarly journals EAGLE: An Interactive Engine/Airframe Life Cycle Cost Model

1982 ◽  
Author(s):  
E. J. Reed ◽  
R. R. Horton ◽  
J. B. Fyfe
Keyword(s):  
Life Cycle ◽  
Life Cycle Cost ◽  
Development Process ◽  
Cost Model ◽  
Aircraft Engine ◽  
Preliminary Design ◽  
Weapon System ◽  
Technology Evaluation ◽  
Advance Technology ◽  
Design Decisions

A major portion of the Life Cycle Cost (LCC) of a modern high technology weapon system is determined by design decisions made very early in the development process. Many of these decisions are so fundamental that later changes become impractical. As a result, a usage-sensitive, interactive aircraft engine LCC model has been developed by Pratt & Whitney Aircraft to evaluate and prioritize potential technology candidates during conceptual/preliminary design. This paper discusses the development of the EAGLE (Engine/Airframe Generalized LCC Evaluator) model, its validation using results from the Advance Technology Engine Studies (ATES), and includes an example engine technology evaluation.

Reduction of life cycle costs for a contemporary helicopter through improvement of reliability and maintainability parameters

2018 ◽  
Vol 35 (2) ◽  
pp. 545-567 ◽  
Author(s):  
Chanchal Ghosh ◽  
J. Maiti ◽  
Mahmood Shafiee ◽  
K.G. Kumaraswamy
Keyword(s):  
Life Cycle ◽  
Life Cycle Cost ◽  
Life Cycle Costs ◽  
Customer Requirements ◽  
Design Data ◽  
Content Type ◽  
Asset Managers ◽  
Operational Data ◽  
Practical Implications ◽  
Potential Area

Purpose The modern helicopters are designed with maximum serviceability and long life expectancy to ensure minimum life cycle cost. The purpose of this paper is to present a framework to incorporate the customer requirements on reliability and maintainability (R&M) parameters into the design and development phase of a contemporary helicopter, and to discuss the way to capture operational data to establish and improve the R&M parameters to reduce life cycle cost. Design/methodology/approach From the analysis, it is established that the reliability and maintainability cost is the major contributor to the life cost. The significant reliability and maintainability parameters which influence R&M cost are identified from analysis. The operational and design data of a contemporary helicopter are collected, compiled and analyzed to establish and improve the reliability and maintainability parameters. Findings The process depicted in the paper is followed for a contemporary helicopter and substantial amount of life cycle cost reduction is observed with improvement of R&M parameters. Practical implications The benefits of this methodology not only reduce life cycle cost but also improve the availability/serviceability through less failure and less time for scheduled maintenance. The methodologies also provide the reliability trends indicating potential area for design improvement. Originality/value The proposed approach assists asset managers to reduce the life cycle costs through improvement of R&M parameters.

A knowledge-based system integrated with numerical analysis tools for aircraft life-cycle design

1998 ◽  
Vol 12 (3) ◽  
pp. 211-229 ◽  
Author(s):  
WILLIAM J. MARX ◽  
DIMITRI N. MAVRIS ◽  
DANIEL P. SCHRAGE
Keyword(s):  
Life Cycle ◽  
Numerical Analysis ◽  
Life Cycle Cost ◽  
Integrated Design ◽  
Cost Estimates ◽  
Transport Aircraft ◽  
Knowledge Based System ◽  
Knowledge Based ◽  
Analysis Tools ◽  
Structural Concept

An integrated design and manufacturing approach allows economic decisions to be made that reflect an entire system design as a whole. To achieve this objective, we have developed and utilized integrated cost and engineering models within a focused design perspective. A framework for the integrated design of an aircraft system with a combined performance and economic perspective is described in this article. This framework is based on the concept of Design Justification using a Design-for-Economics approach. We have developed a knowledge-based system that can be used to evaluate aircraft structural concept material and process selections. The framework consists of the knowledge-based system, integrated with numerical analysis tools including an aircraft performance/sizing code and a life-cycle cost analysis code. Production cost estimates are applied for evaluation of process trades at the subcomponent level of design. Life-cycle cost estimates are used for evaluation of process trades at the system level. Results of a case study are presented for several advanced wing structural concepts for a future supersonic commercial transport aircraft. Cost versus performance studies indicate that a high-speed civil transport aircraft with a hybrid wing structural concept, though more expensive to manufacture than some homogeneous concepts, can have lower direct operating costs due to a lower take-off gross weight and less mission fuel required.

Life-cycle cost analysis of building wall and insulation materials

2019 ◽  
Vol 43 (5) ◽  
pp. 428-455 ◽  
Author(s):  
Dileep Kumar ◽  
Patrick X.W. Zou ◽  
Rizwan Ahmed Memon ◽  
MD Morshed Alam ◽  
Jay G Sanjayan ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Life Cycle ◽  
Life Cycle Cost ◽  
Construction Materials ◽  
Building Construction ◽  
Life Cycle Cost Analysis ◽  
Insulation Materials ◽  
Insulation Thickness ◽  
Wall Materials ◽  
Optimum Insulation Thickness

Heat transfer through building opaque envelope is responsible for approximately half of the total heat loss and gain to and from the surroundings. Therefore, insulation materials are commonly used in the building envelope to reduce the heat transfer. Recently, lightweight wall materials with lower thermal conductivity are used in construction along with the commonly used materials such as heavy concrete and earthen materials. In this perspective, there is a need to understand the optimum insulation thickness for different types of building construction materials to minimize unnecessary usage of insulation materials. This study investigated the optimum insulation thickness for different construction materials following a life-cycle approach, where an analytical optimization methodology based on the degree-days method and life-cycle cost analysis was used. In total, 4 insulation materials and 15 building construction materials were considered in the optimization study. The objective function was to minimize life-cycle cost corresponding to the decision variables including insulation thickness and the thermal conductivity of insulation and wall materials. The results showed that the use of insulation in lightweight wall materials is not economically feasible because of their negligible cost-saving potential (below US$2.5/m2-year). However, the walls with heavy concrete and earthen materials that have high thermal mass must be insulated due to their highest cost-saving potential (US$14–26.39/m2-year).

scholarly journals ESTIMASI BIAYA DAUR HIDUP DAN OPTIMISASI HARGA PESAWAT TERBANG

2012 ◽  
Vol 9 (1) ◽  
Author(s):  
Rais Zain ◽  
Odi Ahyarsi
Keyword(s):  
Life Cycle ◽  
Cost Analysis ◽  
Life Cycle Cost ◽  
Optimization Problems ◽  
Object Oriented ◽  
Aircraft Design ◽  
Conceptual Design Phase ◽  
Object Oriented Approach ◽  
Cost Object ◽  
Oriented Approach

 Since the conceptual design phase, the estimate of airplane life cycle cost (LCC) is carried out to support a decision making process. The LCC consist of research, development, testing, and evaluation cost, where an airplane estimated price (AEP) is a part of this calculation. Furthermore, AEP is employed as a non linear objective funtion for developing a constrained optimization algorthm. Rosen’s gradient projection is applyed in the development of computer program named Cost Analysis implementing object oriented approach on Microsoft Visual C++ 6.0. In order to verify the application, some data of Ourania jet airplane were utilized for carrying out a case study. The result of Cost Analysis shows that the estimated LCC are similar to the reference. Also, the optimization problems can be solved by Rosen’s algorithm less than ten iterations. Keywords:Conceptual aircraft design, Life cycle cost, Object oriented approach, Visual C++

scholarly journals Life Cycle Cost as a Propulsion System Design Consideration

1977 ◽  
Author(s):  
C. E. Curry
Keyword(s):  
Life Cycle ◽  
Life Cycle Cost ◽  
System Development ◽  
Aircraft Engine ◽  
Propulsion System ◽  
Development Programs ◽  
Math Model ◽  
Support Costs ◽  
Heavy Lift ◽  
Turboshaft Engine

This paper deals with applying Life Cycle Cost (LCC) and Design To Cost (DTC) principles to aircraft engine programs. The dynamic driving elements of LCC are identified with an example of direct application to a deterministic computer model. This model was used as the principal tool to project operating and support costs for the XT701 turboshaft engine in conjunction with the U.S. Army Heavy Lift Helicopter Development that featured a specific DTC-related award fee in the contract. The overall methodology of LCC and DTC supported by the math model earned a Superior evaluation with an unprecedented 100 percent award fee for this kind of application. The customer audit, in support of the performance award, supports the conclusion that computer models can be used to enhance the LCC aspects of propulsion system development programs.

scholarly journals METHODOLOGICAL BASIS FOR ESTIMATING THE LIFE CYCLE COST OF AIRCRAFT ENGINE, TAKING INTO ACCOUNT THE ATTENDANT RISKS

2020 ◽  
pp. 121-128
Author(s):  
E. A. Ozdoeva ◽  
O. A. Smolyakov
Keyword(s):  
Risk Assessment ◽  
Life Cycle ◽  
Life Cycle Cost ◽  
Aircraft Engine ◽  
Economic Research ◽  
Typical Structure ◽  
Stage Of Development ◽  
The Creation ◽  
Risk Assessment Methodology ◽  
Engine Development

The formation and development of the main areas of technical and economic research in the field of aircraft engine building have been considered. A typical structure of the life cycle cost of an aircraft engine has been presented and typical tasks in the field of technical and economic efficiency, solved at different stages of the cycle, have been described. Also the method used to solve these problems at the stage of development work on the creation of the engine has been considered. The purpose of the study is to develop a risk assessment methodology for the creation of an aircraft engine, as well as its software implementation with subsequent integration into an existing design product. At this stage, it is necessary to describe clearly the algorithm that will be the basis for the risk assessment of the aircraft engine development.

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