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.

A Method for Determining the Conversion Factors to Convert Gas Turbine Engine Parameters to Normal Values Based on Test Results in a Thermal Pressure Chamber

2019 ◽  
pp. 36-48
Author(s):  
V.A. Grigoriev ◽  
D.S. Kalabukhov
Keyword(s):  
Gas Turbine ◽  
Normal Values ◽  
Gas Turbine Engine ◽  
Pressure Chamber ◽  
Test Results ◽  
Ambient Conditions ◽  
Thermal Pressure ◽  
Output Data ◽  
Conversion Factors ◽  
Turbine Engine

The article presents a method for determining the normalizing coefficients of recalculation of the main technical parameters of a gas turbine engine when undergoing production testing. The method is based on the application of methods for planning a design experiment. The mathematical models of the output data of the engine, necessary for carrying out such an experiment, were obtained by means of static processing of the protocols of the previous tests that contained the results of direct measurements of the parameters in a thermal pressure chamber. The ambient conditions (atmospheric pressure and temperature) and the operating parameters (rotational frequency and effective power of the engine) were selected as variable factors of the experimental design. Depending on these factors, the normal values of the parameters and the normalizing conversion factors for fuel consumption, air consumption, gas temperatures in the flow part of the engine and other output data were determined analytically. The method was demonstrated by processing test results of the 9I56 engine.

Conversion of the AE 1107C From the V-22 Osprey Application to Marine Service

2013 ◽  
Author(s):  
Zechariah D. Green ◽  
Sean Padfield ◽  
Andrew F. Barrett ◽  
Paul G. Jones
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Naval Vessel ◽  
Turbine Engine ◽  
The Us ◽  
Technical Risk ◽  
Turbine Design ◽  
System Designs

This paper presents a study on the conversion of the Rolls-Royce AE 1107C V-22 Osprey gas turbine engine into the MT7 Ship-to-Shore Connector (SSC) marine gas turbine engine. The US Navy led SSC design requires a propulsion and lift gas turbine rated at 5,230 shaft horsepower, which the AE 1107C variant MT7 is capable of providing with margin on power and specific fuel consumption. The MT7 leverages the AE family of engines to provide a propulsion and lift engine solution for the SSC craft. Extensive testing and analysis completed during the AE 1107C development program aided in the robust gas turbine design required to meet the needs of the SSC program. Requirements not met by the AE 1107C configuration were achieved with designs based on the AE family of engines and marine grade sub-system designs. Despite the fact that system integration and testing remain as key activities for integrating the MT7 with the SSC craft, conversion of the AE 1107C FAA certified engine into an American Bureau of Shipping Naval Vessel Rules Type Approved MT7 engine provides a low technical risk alternative for the demanding requirements of the SSC application.

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.

Enhanced TF40B Gas Turbine Engine Bleed Air Anti-Ice System (BAAS) Development

2004 ◽  
Author(s):  
Roger Yee ◽  
Lee Myers
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Lessons Learned ◽  
Life Extension ◽  
Cold Weather ◽  
Development Effort ◽  
Engine Control ◽  
Turbine Engine ◽  
Service Life Extension

The Landing Craft Air Cushion (LCAC) Service Life Extension Program (SLEP) upgrades the current TF40B gas turbine engine and analog control system to an Enhanced TF40B (ETF40B) gas turbine with a Full Authority Digital Engine Control (FADEC) system. This upgrade and enhancement will provide additional engine horsepower, increased engine reliability, modern digital engine control equipment, and a Bleed Air Anti-Ice System (BAAS) for the LCAC during cold weather operations. The original permanent BAAS system for the SLEP configured LCAC has been redesigned as a “removable kit” to reduce overall craft weight and to minimize maintenance for the crews. The development has been an ongoing effort between the Navy, Textron Marine & Land Systems who is the LCAC craft builder, and Vericor Power Systems, who is the ETF40B manufacturer. This paper will document and outline the BAAS development effort and the many lessons learned during the design of a prototype BAAS system for the ETF40B engine.

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.

Development of the Garrett GTPF990: A 5000-Horsepower Marine and Industrial Gas Turbine Engine

1978 ◽  
Author(s):  
E. L. Wheeler
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Gas Turbine Engine ◽  
Status Report ◽  
Test Results ◽  
Turbine Engine ◽  
Endurance Testing ◽  
Qualification Testing ◽  
Industrial Gas Turbine ◽  
Engine Development

The Garrett GTPF990 gas turbine engine is being developed under a U.S. Navy contract to fulfill both propulsion and generator drive repuirements. This is a unique second-generation marine engine that is not derived from an aircraft engine counterpart. The engine development is nearing completion, endurance testing has started, and all other qualification testing has been conducted. This paper is a development status report. A description of the engine and special maintenance features is presented. Emphasis is placed on qualification test results, development test experience, and the resulting design improvements.

Analysis of Using the M-Cycle Regenerative-Humidification Process on a Gas Turbine

2014 ◽  
Author(s):  
P. E. Jenkins ◽  
M. Cerza ◽  
Mohammad M. Al Saaid
Keyword(s):  
Gas Turbine ◽  
System Performance ◽  
Gas Turbine Engine ◽  
Brayton Cycle ◽  
Test Results ◽  
Turbine Engine ◽  
Performance Curves ◽  
Air Cooler ◽  
Net Power Output ◽  
Turbine Exhaust

This investigation focused on the analysis of using the Maisotsenko Cycle (M-Cycle) to improve the efficiency of a gas turbine engine. By combining the Maisotsenko Cycle (M-Cycle) with an open Brayton cycle, a new cycle, is known as the Maisotsenko Combustion Turbine Cycle (MCTC), was formed. The MCTC used an Indirect Evaporative Air Cooler as a saturator with a gas turbine engine. The saturator was applied on the side of the turbine exhaust (M-Cycle#2) in the analysis. The analysis included calculations and the development of an Engineering Equation Solver (EES) code to model the MCTC system performance. The resulting performance curves were graphed to show the effects of several parameters on the thermal efficiency and net power output of the gas turbine engine. The models were also compared with actual experimental test results from a gas turbine engine. Conclusions and discussions of results are also given.

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.

scholarly journals Developments in New Gas Turbine Engine Demonstrator Programs

1986 ◽  
Author(s):  
Edward T. Johnson ◽  
David D. Klassen
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Full Scale ◽  
Lessons Learned ◽  
Turbine Engine ◽  
Applied Technology ◽  
Technology Level ◽  
Engine Development ◽  
Technology Demonstrator

Since 1967 the Aviation Applied Technology Directorate (AATD) has sponsored four technology demonstrator engine programs. These programs have been established for purposes of verifying the engine technology level appropriate for the initiation of full scale engine development. While these were all highly successful, significant improvements have evolved in the approach to these programs. This paper discusses this evolution, lessons learned, and results.

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