Damage tolerant design - An approach to reducing the life cycle cost of gas turbine engine disks

1979 ◽  
Author(s):  
C. MEECE ◽  
C. SPAETH
Keyword(s):  
Life Cycle ◽  
Gas Turbine ◽  
Life Cycle Cost ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Damage Tolerant

Introducing Life Cycle Cost Analysis in an Undergraduate Gas Turbine Engine Design Capstone Course

2020 ◽  
Author(s):  
Aaron R. Byerley ◽  
Steve A. Brandt
Keyword(s):  
Life Cycle ◽  
Cost Analysis ◽  
Gas Turbine ◽  
Life Cycle Cost ◽  
Gas Turbine Engine ◽  
Production Costs ◽  
Life Cycle Cost Analysis ◽  
Decision Matrix ◽  
Turbine Engine ◽  
Engine Design

Abstract The purpose of this paper is to introduce the basics of life cycle cost analysis for use in an undergraduate, senior-level capstone, gas turbine engine design course. This paper will support the heightened interest within the military acquisition community that now requires life cycle cost analysis to be included in the proposals submitted by defense contractors. The capstone design course includes both the gas turbine engine cycle selection and engine component design that supports a particular aircraft application. While the students have been taught how to estimate the fuel costs, engine development costs, and the time-varying production costs of engines, they have not yet been provided instruction on how to factor all three types of costs into an engineering economics, time-value-of-money, present value analysis. This paper will fill that gap and serve as a resource for the students who must now consider life cycle cost as an element in their design decision matrix along with engine performance, technical risk, and development time. The typical case compares an engine where the upfront development and production costs associated with a more advanced level of technology are high early on in the life cycle but over time has a lower fuel cost compared to an engine with a lower development and production cost but with a higher fuel cost. This paper illustrates how the aerodynamics, thermodynamics, and engineering economics can be brought together to inform and defend a decision about which of the two (or more) alternatives is best. The engineering economic analysis is spreadsheet based and uses inflation adjusted, total annual costs to calculate the present value for use in a decision matrix.

Gas Turbine Engine Disk Retirement-for-Cause: An Application of Fracture Mechanics and NDE

1980 ◽  
Author(s):  
C. G. Annis ◽  
M. C. VanWanderham ◽  
J. A. Harris ◽  
D. L. Sims
Keyword(s):  
Fracture Mechanics ◽  
Gas Turbine ◽  
Life Cycle Cost ◽  
Energy Savings ◽  
Cost Savings ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Turbine Disks ◽  
Full Life ◽  
Engine Components

Historically, gas turbine engine disks are retired when they accrue an analytically determined lifetime where the first fatigue crack per 1000 disks could be expected. By definition then, 99.9 percent of these components are being retired prematurely. Retirement-for-Cause (RFC) is a procedure, based on Fracture Mechanics, which would allow safe utilization of the full life capacities of each individual disk. Since gas turbine disks are among the most costly of engine components, adopting a RFC philosophy could result in substantial systems life cycle cost savings. These would accrue from reduced replacement costs, conservation of strategic materials such as cobalt, and energy savings.

Integration of the WR-21 Intercooled Recuperated Gas Turbine Into the Royal Navy Type 45 Destroyer

2001 ◽  
Author(s):  
Steven J. McCarthy ◽  
Ian Scott
Keyword(s):  
Gas Turbine ◽  
Distribution System ◽  
Life Cycle Cost ◽  
Electric Propulsion ◽  
Electrical Power ◽  
The United States ◽  
Gas Turbine Engine ◽  
Prime Mover ◽  
Royal Navy ◽  
Turbine Engine

The WR-21 gas turbine engine will be employed by the Royal Navy and potentially by the United States and French Navies in their future Integrated Full Electric Powered Surface Combatants. The WR-21 is an advanced cycle gas turbine that will not only meet the high power generator prime mover requirements of these ships but also offer an efficient cruise generator engine in one power dense package. The engine gives ship designers the freedom to procure, install and maintain one engine to power the vessel over its entire operating profile in place of the traditional two engine ‘cruise’ and ‘boost’ fit. Warship operators will also have a new freedom to configure the warship propulsion plant to return unprecedented Platform Life Cycle Cost reductions in peacetime while retaining operational capability in time of conflict. The Royal Navy is the first user of the WR-21 Intercooled and Recuperated (ICR) gas turbine engine in its Type 45 Area Defense destroyer. The vessel is a 6000 tonne monohull, fitted with an integrated electric propulsion plant comprising two WR-21 Gas Turbine Alternators (GTAs), the prime mover side of which are capable of delivering 25 MW (ISO) and the Alternator side of which is rated at 21.6 MWe (0.9 pf lagging), 4.16KVA. These GTAs in combination with a pair of diesel generators rated at around 2 MWe (0.9 pf lagging) will provide electrical power to two 20 MWe (0.9 pf lagging) 4.16 KVA electric propulsion motors and to the ship’s non propulsion consumer electrical distribution system. Any combination of generator set can provide any consumer with electrical power. This flexibility of propulsion plant configuration will demand a step change in operating culture if its ultimate benefits are to be truly harnessed. Every part of warship propulsion and gas turbine engine operating philosophy must be examined to check its relevance in the modern machinery outfit. The engines themselves must be scrutinized to ensure that they can fulfill the requirements of true ship generation machinery and are not regarded as ‘propulsion generators’. In a Warship that has only four sources of electrical power the principles of survivability and prime mover independence are fundamental.

Life Cycle Performance Estimation and In-Flight Health Monitoring for Gas Turbine Engine

2016 ◽  
Vol 138 (9) ◽  
Author(s):  
Feng Lu ◽  
Wenhua Zheng ◽  
Jinquan Huang ◽  
Min Feng
Keyword(s):  
Life Cycle ◽  
Anomaly Detection ◽  
Gas Turbine ◽  
Rapid Prototype ◽  
Gas Turbine Engine ◽  
Performance Estimation ◽  
Prototype System ◽  
Turbine Engine ◽  
Abnormal Detection ◽  
Rapid Prototype System

A long-term gas-path fault diagnosis and its rapid prototype system are presented for on-line monitoring of a gas turbine engine. Toward this end, a nonlinear hybrid model-based performance estimation and abnormal detection method are proposed in this paper. An adaptive extended Kalman particle filter (AEKPF) estimator is developed and used to real time estimate engine health parameters, which depict gas turbine performance degradation condition. The health parameter estimators are then pushed into a buffer memory and for periodical renewing baseline model (BM) performance, and the BM is utilized to detect engine anomaly over its life course. The threshold in abnormal detection schemes is adapted to the modeling errors during the engine lifetime. The rapid prototyping system is designed and built up based on the National Instrument (NI) CompactRIO (CRIO) for evaluating gas turbine engine performance estimation and anomaly detection. A number of experiments are carried out to demonstrate the advantages of the proposed abnormal detection scheme and effectiveness of the designed rapid prototype system to the problem of gas turbine life cycle anomaly detection.

Gas Turbine Engine Disk Retirement-for-Cause: An Application of Fracture Mechanics and NDE

1981 ◽  
Vol 103 (1) ◽  
pp. 198-200 ◽  
Author(s):  
C. G. Annis ◽  
M. C. VanWanderham ◽  
J. A. Harris ◽  
D. L. Sims
Keyword(s):  
Fracture Mechanics ◽  
Gas Turbine ◽  
Life Cycle Cost ◽  
Energy Savings ◽  
Cost Savings ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Turbine Disks ◽  
Full Life ◽  
Engine Components

Historically, gas turbine engine disks are retired when they accrue an analytically determined lifetime where the first fatigue crack per 1000 disks could be expected. By definition then, 99.9 percent of these components are being retired prematurely. Retirement-for-cause (RFC) is a procedure, based on fracture mechanics, which would allow safe utilization of the full life capacities of each individual disk. Since gas turbine disks are among the most costly of engine components, adopting a RFC philosophy could result in substantial systems life cycle cost savings. These would accrue from reduced replacement costs, conservation of strategic materials such as cobalt, and energy savings.

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