Surface Damage Tolerance Analysis of a Gas Turbine Engine Rotor

2005 ◽  
Author(s):  
Ahsan Jameel
Keyword(s):  
Gas Turbine ◽  
Tolerance Analysis ◽  
Surface Damage ◽  
Gas Turbine Engine ◽  
Jet Engines ◽  
Commercial Aircraft ◽  
Design Assessment ◽  
Turbine Engine ◽  
Southwest Research Institute ◽  
Probability Of Fracture

DARWIN™ (Design Assessment of Reliability With INspection) is a simulation-based computer program for probabilistic fatigue life prediction of rotors and disks in commercial aircraft jet engines. This program is being developed by Southwest Research Institute® (SwRI®) and a team of major aircraft gas turbine engine manufacturers (General Electric, Pratt & Whitney, Honeywell, and Rolls Royce Indianapolis) as a major research and development initiative. This paper is a presentation of the experience of Honeywell in the use of DARWIN to assess probability of fracture (POF) due to surface damage in a highly stressed bolthole in a nickel component.

Mitigation of Fretting Fatigue Damage in Blade and Disk Pressure Faces With Low Plasticity Burnishing

2007 ◽  
Author(s):  
Paul S. Preve´y ◽  
N. Jayaraman ◽  
Ravi A. Ravindranath ◽  
Michael Shepard
Keyword(s):  
Gas Turbine ◽  
Design Method ◽  
Surface Damage ◽  
Gas Turbine Engine ◽  
Cnc Machine Tools ◽  
Cnc Machine ◽  
Residual Stress Field ◽  
Treatment Technology ◽  
Turbine Engine ◽  
Low Plasticity Burnishing

Low Plasticity Burnishing (LPB) is now established as a surface enhancement technology capable of introducing through-thickness compressive residual stresses in the edges of gas turbine engine blades and vanes to mitigate foreign object damage (FOD). The “Fatigue Design Diagram” (FDD) method has been described and demonstrated to determine the depth and magnitude of compression required to achieve the optimum high cycle fatigue (HCF) strength, and to mitigate a given depth of damage characterized by the fatigue stress concentration factor, kf. LPB surface treatment technology and the FDD method have been combined to successfully mitigate a wide variety of surface damage ranging from FOD to corrosion pits in titanium and steel gas turbine engine compressor and fan components. LPB mitigation of fretting induced damage in Ti-6AL-4V in laboratory samples has now been extended to fan and compressor components. LPB tooling technology recently developed to allow the processing of the pressure faces of fan and compressor blade dovetails and mating disk slots is described. Fretting induced micro-cracks that form at the pressure face edge of bedding on both the blade dovetail and the dovetail disk slots in Ti-6-4 compressor components can now be arrested by the introduction of deep stable compression in conventional CNC machine tools during manufacture or overhaul. The compressive residual stress field design method employing the FDD approach developed at Lambda Technologies is described in application to mitigate fretting damage. The depth and magnitude of compression and the fatigue and damage tolerance achieved are presented. It was found that microcracks as deep as 0.030 in., (0.75 mm) large enough to be readily detected by current NDI technology, can be fully arrested by LPB. The depth of compression achieved could allow NDI screening followed by LPB processing of critical components to reliably restore fatigue performance and extend component life.

Method for calculating the thrust and specific thrust of a double-flow gas turbine engine based on the results of tests at the laboratory unit «Flame»

2021 ◽  
pp. 58-64
Author(s):  
S.M. Sergeev ◽  
◽  
V.A. Kudriashov ◽  
N.V. Petrukhin ◽  
◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Similarity Criteria ◽  
Fuel Quality ◽  
Jet Engines ◽  
Laboratory Unit ◽  
Turbine Engine ◽  
Specific Thrust ◽  
The Cost

The main technical characteristics of jet engines depend on the fuel quality: thrust and fuel consumption. As a rule, the comparative assessment of real engines is carried by specific values. Specific thrust is one of the most important parameters of the gas turbine engine (GTE). The larger it is, the smaller the required air flow rate through the engine at a given thrust and therefore its dimensions and mass. To date, a system for evaluating the performance properties of fuels based on qualification methods has been created. However, these methods do not allow calculating the thrust and specific thrust of the engine and potentially assessing the effect of fuels on these characteristics. Therefore, the issues of efficient use of fuels for GTE are solved almost exclusively on the basis of tests at testing units with full-scale engines, which are carried out repeatedly, which leads to a significant increase in the cost of testing. The article proposes a method for calculating the thrust and specific thrust of a double-flow gas turbine engine according to the results of tests at a constant volume laboratory unit of bypass type “Flame”. The method is based on modeling the engine operating conditions using the similarity criteria of the bench reactor and the real engine and allows reducing significantly the material and time costs for testing. The experimental of the combustion characteristics of hydrocarbon fuels and the rated values of their thrust and specific thrust for a double-flow gas turbine engine are presented.

ABS NVR Type Approval of the Rolls-Royce Naval Marine Model MT5S Gas Turbine Engine and the RR4500 Generator Set

2014 ◽  
Author(s):  
Peter Lahm ◽  
Jack Halsey
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Lessons Learned ◽  
Test Results ◽  
Approval Process ◽  
Naval Vessel ◽  
Design Assessment ◽  
Turbine Engine ◽  
Type Approval ◽  
Type Approval Testing

This treatise examines the activities required to Type Approve the MT5S gas turbine engine and RR4500 generator set to the American Bureau of Shipping Naval Vessel Rules (ABS NVR). Detailed accounts of the various phases of the approval process and challenges encountered therein are presented. The methods utilized to achieve ABS design assessment and the process of Type Approval testing is presented. Design assessment and Type Approval test results are summarized. A discourse containing lessons learned and corrective measures for future Type Approval efforts is included.

scholarly journals Improving Survivability of Aircraft from Uncontained Gas Turbine Engine Failures

2011 ◽  
Vol 133 (08) ◽  
pp. 56-57
Author(s):  
Chris Adams ◽  
John Manion
Keyword(s):  
Gas Turbine ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Assessment Model ◽  
Hazard Evaluation ◽  
Commercial Aircraft ◽  
Turbine Engine ◽  
Geometry Model ◽  
Us Military ◽  
Aircraft Component

This article describes new measures to improve survivability of aircraft from uncontained gas turbine engine failures. The US military has adopted a common tool—Uncontained Engine Debris Damage Assessment Model (UEDDAM)—for its methodology to consider uncontained events in a more realistic manner. UEDDAM can handle the analysis for the release of the primary rotor-disk segment plus smaller engine debris fragments in directions out of the plane of rotation. The UEDDAM code requires an input of a three-dimensional geometric description of aircraft component positions within the aircraft and thus, in relationship to each other. The description uses a specific input format. Adopting an assessment methodology, like UEDDAM, results in a universal standard and uniformity of debris hazard evaluation across the involved agencies. Maintaining the 3D aircraft geometry model and its components/system functional flow data generated by aircraft manufacturers during their initial hazard assessment would simplify later debris hazard reassessments required by maintenance, repair, or military-modification to a commercial aircraft.

Probabilistic High-Cycle Fretting Fatigue Assessment of Gas Turbine Engine Components

2011 ◽  
Author(s):  
Kwai S. Chan ◽  
Michael P. Enright ◽  
Patrick J. Golden ◽  
Samir Naboulsi ◽  
Ramesh Chandra ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Real Life ◽  
Fretting Fatigue ◽  
Gas Turbine Engine ◽  
Rotating Stall ◽  
Worst Case ◽  
Design Assessment ◽  
Turbine Engine ◽  
Engine Components

High-cycle fatigue (HCF) is arguably one of the costliest sources of in-service damage in military aircraft engines. HCF of turbine blades and disks can pose a significant engine risk because fatigue failure can result from resonant vibratory stresses sustained over a relatively short time. A common approach to mitigate HCF risk is to avoid dangerous resonant vibration modes (first bending and torsion modes, etc.) and instabilities (flutter and rotating stall) in the operating range. However, it might be impossible to avoid all the resonance for all flight conditions. In this paper, a methodology is presented to assess the influences of HCF loading on the fracture risk of gas turbine engine components subjected to fretting fatigue. The methodology is based on an integration of a global finite element analysis of the disk-blade assembly, numerical solution of the singular integral equations using the CAPRI (Contact Analysis for Profiles of Random Indenters) and Worst Case Fret methods, and risk assessment using the DARWIN (Design Assessment of Reliability with Inspection) probabilistic fracture mechanics code. The methodology is illustrated for an actual military engine disk under real life loading conditions.

TEMPER—A Gas-Path Analysis Tool for Commercial Jet Engines

1994 ◽  
Vol 116 (1) ◽  
pp. 82-89 ◽  
Author(s):  
D. L. Doel
Keyword(s):  
Path Analysis ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Analysis Tool ◽  
Jet Engines ◽  
Effective Technique ◽  
Turbine Engine ◽  
Scope Definition ◽  
Research Areas ◽  
Improved Algorithm

Almost from the inception of the gas turbine engine, airlines and engine manufacturers have sought an effective technique to determine the health of the gas-path components (fan, compressors, combustor, turbines) based on available gas-path measurements. The potential of such tools to save money by anticipating the need for overhaul and providing help in work scope definition is substantial, provided they produce reliable results. This paper describes a modern gas-path analysis tool (GE’s TEMPER program), discusses the benefits and problems experienced by current TEMPER users, and suggests promising research areas that may lead to an improved algorithm.

Probabilistic High-Cycle Fretting Fatigue Assessment of Gas Turbine Engine Components

2012 ◽  
Vol 134 (6) ◽  
Author(s):  
Kwai S. Chan ◽  
Michael P. Enright ◽  
Patrick J. Golden ◽  
Samir Naboulsi ◽  
Ramesh Chandra ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Real Life ◽  
Fretting Fatigue ◽  
Gas Turbine Engine ◽  
Rotating Stall ◽  
Worst Case ◽  
Design Assessment ◽  
Turbine Engine ◽  
Engine Components

High-cycle fatigue (HCF) is arguably one of the costliest sources of in-service damage in military aircraft engines. HCF of turbine blades and disks can pose a significant engine risk because fatigue failure can result from resonant vibratory stresses sustained over a relatively short time. A common approach to mitigate HCF risk is to avoid dangerous resonant vibration modes (first bending and torsion modes, etc.) and instabilities (flutter and rotating stall) in the operating range. However, it might be impossible to avoid all the resonance for all flight conditions. In this paper, a methodology is presented to assess the influences of HCF loading on the fracture risk of gas turbine engine components subjected to fretting fatigue. The methodology is based on an integration of a global finite element analysis of the disk-blade assembly, numerical solution of the singular integral equations using the CAPRI (Contact Analysis for Profiles of Random Indenters) and Worst Case Fret methods, and risk assessment using the DARWIN (Design Assessment of Reliability with Inspection) probabilistic fracture mechanics code. The methodology is illustrated for an actual military engine disk under real life loading conditions.

scholarly journals TEMPER: A Gas-Path Analysis Tool for Commercial Jet Engines

1992 ◽  
Author(s):  
David L. Doel
Keyword(s):  
Path Analysis ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Analysis Tool ◽  
Jet Engines ◽  
Effective Technique ◽  
Turbine Engine ◽  
Scope Definition ◽  
Research Areas ◽  
Improved Algorithm

Almost from the inception of the gas turbine engine, airlines and engine manufacturers have sought an effective technique to determine the health of the gas-path components (fan, compressors, combustor, turbines) based on available gas-path measurements. The potential of such tools to save money by anticipating the need for overhaul and providing help in work scope definition is substantial, provided they produce reliable results. This paper describes a modern gas-path analysis tool (GE’s TEMPER1 program), discusses the benefits and problems experienced by current TEMPER users, and suggests promising research areas that may lead to an improved algorithm.

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