Analysis of Gas Turbine Engine Failure Modes.

2011 ◽

Vol 133 (8) ◽

Cited By ~ 4

Author(s):

Michael P. Enright ◽

R. Craig McClung

Keyword(s):

Gas Turbine ◽

System Reliability ◽

Failure Modes ◽

Gas Turbine Engine ◽

Probabilistic Framework ◽

Turbine Engine ◽

Nickel Based Superalloy ◽

Kaplan Meier ◽

Reliability Methods ◽

Failure Probabilities

Some rotor-grade gas turbine engine materials may contain multiple types of anomalies such as voids and inclusions that can be introduced during the manufacturing process. The number and size of anomalies can be very different for the various anomaly types, each of which may lead to premature fracture. The probability of failure of a component with multiple anomaly types can be predicted using established system reliability methods provided that the failure probabilities associated with individual anomaly types are known. Unfortunately, these failure probabilities are often difficult to obtain in practice. In this paper, an approach is presented that provides treatment for engine materials with multiple anomalies of multiple types. It is based on a previous work that has been extended to address the overlap among anomaly type failure modes using the method of Kaplan–Meier and is illustrated for risk prediction of a nickel-based superalloy. The results can be used to predict the risk of general materials with multiple types of anomalies.

Download Full-text

A Probabilistic Framework for Gas Turbine Engine Materials With Multiple Types of Anomalies

Volume 6: Structures and Dynamics, Parts A and B ◽

10.1115/gt2010-23618 ◽

2010 ◽

Cited By ~ 1

Author(s):

Michael P. Enright ◽

R. Craig McClung

Keyword(s):

Gas Turbine ◽

System Reliability ◽

Failure Modes ◽

Gas Turbine Engine ◽

Probabilistic Framework ◽

Turbine Engine ◽

Nickel Based Superalloy ◽

Kaplan Meier ◽

Reliability Methods ◽

Failure Probabilities

Some rotor-grade gas turbine engine materials may contain multiple types of anomalies such as voids and inclusions that can be introduced during the manufacturing process. The number and size of anomalies can be very different for the various anomaly types, each of which may lead to premature fracture. The probability of failure of a component with multiple anomaly types can be predicted using established system reliability methods provided that the failure probabilities associated with individual anomaly types are known. Unfortunately, these failure probabilities are often difficult to obtain in practice. In this paper, an approach is presented that provides treatment for engine materials with multiple anomalies of multiple types. It is based on previous work that has extended to address the overlap among anomaly type failure modes using the method of Kaplan-Meier, and is illustrated for risk prediction of a nickel-based superalloy. The results can be used to predict the risk of general materials with multiple types of anomalies.

Download Full-text

Development of the WR-21 Gas Turbine Recuperator

Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award; General ◽

10.1115/99-gt-314 ◽

1999 ◽

Cited By ~ 1

Author(s):

Robert C. Sanders ◽

George C. Louie

Keyword(s):

Gas Turbine ◽

Failure Modes ◽

Waste Heat ◽

Operating Experience ◽

Gas Turbine Engine ◽

Analytical Models ◽

Royal Navy ◽

Engine Exhaust ◽

Turbine Engine ◽

Technical Requirements

WR-21 is an intercooled and recuperated (ICR) gas turbine engine being developed by the U. S. Navy (USN) with contributions from the Royal Navy and the French Navy. A key component of the WR-21 engine is the recuperator used to recover waste heat from engine exhaust gas. The recuperator is being designed and fabricated by AlliedSignal Aerospace Company under subcontract to Northrop Grumman Marine Services, the prime contractor for the WR-21 gas turbine engine. One of the most challenging developmental items for the WR-21 engine has proven to be the recuperator. This paper discusses the development of the recuperator, including the advanced development (AD) recuperator which failed after a few hours of operation, the limited operating unit (LOU) recuperator which has supported much of the WR-21 engine development testing and the engineering development model (EDM) recuperator which will be used for a 3000 hour engine endurance test. Included is an overview of USN technical requirements for the recuperator and a review of operating experience with the AD and LOU recuperators. Failure modes that have been experienced are discussed in detail, including root cause evaluations and design modifications. Steps taken to extend the life of the LOU recuperator are discussed. In addition, testing (both single core and full size recuperator) and analytical models that have been used to improve the design and reliability of the recuperator are addressed.

Download Full-text

Research of Small Gas Turbine Engine Control Logic by Engine Failure Mode Simulation

Journal of the Korean Society of Propulsion Engineers ◽

10.6108/kspe.2021.25.2.088 ◽

2021 ◽

Vol 25 (2) ◽

pp. 88-97

Author(s):

Kyungjae Lee ◽

Sunguk Kim ◽

Kyeungmi Back ◽

Dongho Rhee ◽

Young Seok Kang ◽

...

Keyword(s):

Gas Turbine ◽

Failure Mode ◽

Gas Turbine Engine ◽

Engine Control ◽

Control Logic ◽

Turbine Engine ◽

Engine Failure

Download Full-text

Rotor Burst Protection Program: Statistics on Aircraft Gas Turbine Engine Rotor Failures That Occurred in U. S. Commercial Aviation During 1973

Volume 1A: General ◽

10.1115/75-gt-12 ◽

1975 ◽

Cited By ~ 1

Author(s):

G. J. Mangano ◽

R. A. DeLucia

Keyword(s):

Gas Turbine ◽

Gas Turbine Engine ◽

Statistical Information ◽

Commercial Aviation ◽

Turbine Engine ◽

Aircraft Gas Turbine Engine ◽

Engine Failure ◽

Causes Of Failure ◽

Engine Rotor

This paper presents statistical information on the aircraft gas turbine engine rotor failures that occurred in U.S. commerical aviation during 1973. Based on FAA data, results are presented that establish (1) the incidence of rotor failure, (2) the type of fragments generated, (3) whether or not these fragments were contained, (4) the causes of failure, (5) where in the engine failure occurred, (6) what engines were affected and (7) what flight conditions prevailed at failure. The rate of uncontained rotor burst was considered to be significantly high.

Download Full-text