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Relevant bibliographies by topics / Rolls-Royce engines

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Academic literature on the topic 'Rolls-Royce engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 17 February 2022

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Journal articles on the topic "Rolls-Royce engines"

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Feilden, G. B. R. "Lionel Haworth. 4 August 1912 — 12 April 2000." Biographical Memoirs of Fellows of the Royal Society 51 (January 2005): 195–220. http://dx.doi.org/10.1098/rsbm.2005.0013.

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Lionel Haworth was one of the leading aero engine designers in the world. After initial training in 1934 to 1936 with the Associated Equipment Company of Southall–the builders of London's buses—he moved to Rolls–Royce, Derby, where he worked until 1963 when he transferred to the Bristol Siddeley engine company, which merged with Rolls–Royce in 1966. Throughout his career he was very much a 'hands on' engineer who insisted in keeping close to work on any new engine for which he was responsible. He worked on Rolls–Royce engines for aircraft ranging from the Meteor to Concorde, his crowning achievement in Derby being the Dart engine, which was an extremely successful, admirably simple turboprop that powered the Vickers Viscount and 11 other aircraft and had a wide influence on the future of civil aviation around the world. In Bristol, as Chief Designer, he took overall responsibility for the Concorde, Harrier and Tornado as well as all other aero engines being developed and built by Rolls–Royce, Bristol, between 1963 and 1977.

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Tipton, Leighton P. J. "Bearing Load Measurements on a 3-Shaft Gas Turbine." Applied Mechanics and Materials 1-2 (September 2004): 225–32. http://dx.doi.org/10.4028/www.scientific.net/amm.1-2.225.

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Axial location bearings are used to carry the load imbalance between the forward thrust of an aero-engine’s compressor and the rearwards drag of the turbine that drives the compressor’s rotation. The large gas turbines manufactured by Rolls-Royce have three independently rotating compressor/turbine stages, namely the low pressure (LP), the intermediate pressure (IP) and high pressure (HP) systems. The load imbalance, or bearing load, associated with each of these systems must be assessed during an engines development phase in order to confirm the reliability of the bearings throughout the operating life of the engine. The methods employed by Rolls-Royce to quantify the bearing loads on their modern range of gas turbines are discussed, including the most recent technique using modified engine structures to act as load measuring devices. Particular note is given to the instrumentation techniques used to record the loads generated by the engine during sea level testing.

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Jarvis, A. F. "XG40—Advanced Combat Engine Technology Demonstrator Program." Journal of Engineering for Gas Turbines and Power 111, no. 2 (April 1, 1989): 193–99. http://dx.doi.org/10.1115/1.3240236.

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Commenced in 1982, the XG40 program is central to the demonstration of Rolls-Royce technology appropriate to the requirements of the advanced combat engine for mid-1990s operation. At the same time, the technology in scaled form is viewed as having wider application than for the advanced combat engine alone. This program is jointly funded by UK MoD and Rolls-Royce. In the paper the concepts and scope of the program are described. Associations with previous research programs and other advanced technology demonstrator programs of Rolls-Royce are stated. To meet the multirole capabilities of the advanced fighter and taking the European requirements in particular, the combat engine must be designed to give enhanced dry thrust, retain good dry specific fuel consumption, and reduce reheated fuel consumption compared with current fighter engines. A thrust/weight ratio of 10:1 is targeted and at the same time, requirements for operating cost, reliability, and durability are stringent. As a demonstrator, XG40 has been designed to meet the foregoing performance requirements. At the same time, advanced materials, manufacturing technology, and design of structures have been incorporated to enable the required levels of reliability, durability, component cost, and weight to be demonstrated. Although a demonstrator, XG40 was designed at a scale judged to be appropriate to the likely next generation European fighter requirement. Thus, the engine is in the 90/95 kN nominal Sea Level Static Combat thrust class. Configuration and design are discussed. XG40 is a total technology demonstration program. Principal modules each have a full-scale aerothermal rig program and appropriate structure rig programs. Apart from rigs, the program, including durability testing, utilizes a number of cores and engines plus spares. Achievements and progress toward milestones are reviewed.

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Skliros, Christos. "A CASE STUDY OF VIBRATION FAULT DIAGNOSIS APPLIED AT ROLLS-ROYCE T-56 TURBOPROP ENGINE." Aviation 23, no. 3 (January 17, 2020): 78–82. http://dx.doi.org/10.3846/aviation.2019.11900.

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Gas turbine engines include a plethora of rotating modules, and each module consists of numerous components. A component’s mechanical fault can result in excessive engine vibrations. Identification of the root cause of a vibration fault is a significant challenge for both engine manufacturers and operators. This paper presents a case study of vibration fault detection and isolation applied at a Rolls-Royce T-56 turboprop engine. In this paper, the end-to-end fault diagnosis process from starting system faults to the isolation of the engine’s shaft that caused excessive vibrations is described. This work contributes to enhancing the understanding of turboprop engine behaviour under vibration conditions and highlights the merit of combing information from technical logs, maintenance manuals and engineering judgment in successful fault diagnosis.

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Stewart, P. A. E. "X-RAY PHOTOGRAMMETRY OF GAS TURBINE ENGINES AT ROLLS-ROYCE." Photogrammetric Record 9, no. 54 (August 26, 2006): 813–21. http://dx.doi.org/10.1111/j.1477-9730.1979.tb00128.x.

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Parker, R., and G. Fedder. "Aircraft engines: a proud heritage and an exciting future." Aeronautical Journal 120, no. 1223 (January 2016): 131–69. http://dx.doi.org/10.1017/aer.2015.6.

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SUMMARYThe 150th anniversary of the Royal Aeronautical Society has seen Rolls-Royce become a global player in aerospace and a champion of British industry. Its products vary from the nimble RR300, powering two-seater helicopters, all the way to the 97,000-pound thrust Trent XWB, powering future variants of the Airbus A350, and the MT30, which provides the propulsion for the Royal Navy's new Queen Elizabeth class aircraft carriers. It has built this range of products derived from the vision and innovation of its talented engineers, spurred on by the guiding principles provided by Henry Royce. This has seen it through times of war, hardship, bankruptcy and fierce competition to emerge as the leading manufacturer of aircraft engines and a provider of power across land and sea. Alongside its products, it has developed pioneering services to support its customers, analysing real-time data to improve the reliability and efficiency of its engines. In keeping with its tradition of innovation, the company is continuing to develop new products and services for the next generation of power systems for land, sea and air.

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Schubert, P. F., D. R. Sheridan, M. D. Cooper, and A. J. Banchieri. "Sensor-Based Analyzer for Continuous Emission Monitoring in Gas Pipeline Applications." Journal of Engineering for Gas Turbines and Power 120, no. 2 (April 1, 1998): 317–21. http://dx.doi.org/10.1115/1.2818123.

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Continuous emissions monitoring of gas turbine engines in pipeline service have typically been monitored using either laboratory derived instruments (CEMS), or predicted using data from low cost sensors on the engines and algorithms generated by mapping engine performance (PEMS). A new cost-effective system developed under a program sponsored by the Gas Research Institute (Chicago) combines the advantages of both systems to monitor engine emissions in gas transmission service. This hybrid system is a sensor-based analyzer that uses a sensor array, including a newly developed NOx sensor, to directly monitor NOx, CO, and O2 emissions at the stack. The gases are measured hot and wet, The new systems were installed and tested on a gas-fired Rolls Royce Spey turbine engine and on Ingersoll-Rand KVG-410 and Cooper GMVH-10 reciprocating engines in gas transmission service. These systems passed the Relative Accuracy Test (Part B) required under U.S. EPA regulations (40 CFR 60).

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DUTCZAK, Jerzy, and Janusz MAGIER. "The assessment of the technical condition of the bearing seals of the rotor shaft in a turbine helicopter engine based on the PM content in the exhaust gases." Combustion Engines 150, no. 3 (September 1, 2012): 44–54. http://dx.doi.org/10.19206/ce-117030.

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The paper presents the method of measurement of the particulate matter in the exhaust gases of a Rolls-Royce Allison 250-C20B turbine engine in the aspect of the assessment of the technical condition of the bearing seals of the rotor shaft. The tests were carried out on 4 engines using a Horiba TEOM 1105 PM analyzer fitted with a mini dilution tunnel – Micro Diluter 6100. The paper also presents the method of determining of the engine technical condition index (bearing seals) developed by the authors based on the data obtained from the measurements. The reliability of the obtained results has also been subjected to evaluation.

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Parker, R., and M. Lathoud. "Green aero-engines: Technology to mitigate aviation impact on environment." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 224, no. 3 (January 12, 2010): 529–38. http://dx.doi.org/10.1243/09544062jmes1515.

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Despite consistent, continued efforts by the aviation industry to reduce emissions, further technological advances are required to mitigate its impact on the global climate. This article first outlines aviation's importance in the global challenge and its specific constraints relative to other industries. It then investigates the current understanding of aviation's climate impact and the ongoing Rolls-Royce efforts to develop technologies to mitigate it. This includes improving the engine's propulsive efficiency, thermal efficiency, and combustion process. This article also discusses paradigm shifts that might redefine the way this industry operates in the global environment.

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Altosole, Marco, Giovanni Benvenuto, Ugo Campora, Michele Laviola, and Raphael Zaccone. "Simulation and performance comparison between diesel and natural gas engines for marine applications." Proceedings of the Institution of Mechanical Engineers, Part M: Journal of Engineering for the Maritime Environment 231, no. 2 (May 2017): 690–704. http://dx.doi.org/10.1177/1475090217690964.

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The article shows the performance comparison between two marine engines, fuelled by natural gas and diesel oil, respectively, both belonging to the ‘Bergen’ engine series of Rolls-Royce Marine, suitable as prime movers for ship propulsion. Two different simulation codes, one for each engine, validated by means of geometrical and performance data provided by the manufacturer, have been developed to extend the comparison to the whole working area of the examined engines. Although the maximum continuous power is very similar (about 2 MW at the same rotational speed), some differences exist in size, efficiency and pollutant emissions of the two types of engines. The reasons are investigated through a specific thermodynamic analysis, aimed to explain such differences, in terms of efficiency and emissions (particularly carbon dioxide), when varying the working conditions. The analysis is carried out by comparing the respective real cycles, at the same working condition, and repeating the comparison for different engine delivered powers and rotational speeds. In addition, a study of the different modes of combustion is developed to explain the major differences found in the emissions of nitrogen oxides.

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Dissertations / Theses on the topic "Rolls-Royce engines"

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Kais, G. "Heat transfer and fluid flow in the high pressure compressor drive cone cavity of an aeroengine." Thesis, University of Sussex, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.344070.

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Unsworth, Kerrie L. "Unpacking innovation : the processes and predictors of individual innovation amongst engineers." Thesis, University of Sheffield, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.366110.

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Lin, Yi-Nuo, and 林以諾. "Off-Wing Maintenance Cost Analysis of Rolls-Royce RB211-535E4 Engines." Thesis, 2016. http://ndltd.ncl.edu.tw/handle/g339g4.

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碩士
國立虎尾科技大學
飛機工程系航空與電子科技碩士班
105
Aircraft is one of the most popular transport vehicles today. Its time-saving, safety and convenience characteristics are driving the rapid development of the aviation industry. In order to enhance the efficiency in current competitive environments, an effective management on the aircraft maintenance costs is required. Aircraft maintenance costs can be divided into three main parts: airframe maintenance, engine maintenance and component maintenance costs. Engine maintenance costs, accounting for over 40% of the total maintenance cost, is the most prominent part. Since engine maintenance is conducted mainly by outsourced overhaul and repair, the evaluation of proper timing for engine shop visit (ESV) as well as the replacement of life-limited parts (LLP) will yield an important impact on the airline''s operations. Current research focuses on the analysis of off-wing engine maintenance costs. A target airline with its Boeing 757 fleet, which includes two Boeing 757-200’s aircrafts equipped with Rolls-Royce RB211-535E4 engines, is chosen as the case study. Main cost items include the workscope of engine shop visit (ESV), life-limited parts (LLP) replacement, probability costs of engine failure and short-term leasing cost of the replacement engine. According to the characteristics of flight sectors of the airline operation and the reliability life of each engine an optimal schedule for each engine shop visit event as well as the LLP items that needs replacement are then evaluated. In this study, we also take into account of the probability costs of engine failure and short-term replacement engine leasing costs. Total budget for each engine shop visit event is calculated. Further analysis includes the average operational costs per flight hour and per flight cycle. The outcome can be applied as a reference to the decision support of airline operations.

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Books on the topic "Rolls-Royce engines"

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Bill, Gunston. Rolls-Royce aero engines. [Wellington, Northamptonshire, England]: P. Stephens, 1989.

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Rubbra, A. A. Rolls-Royce piston aero engines: A designer remembers. Derby, England: Rolls-Royce Heritage Trust, 1990.

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Dick, Foster-Pegg, Birch David 1939-, and Rolls-Royce Heritage Trust, eds. The Rolls-Royce Crecy. Derby: Rolls-Royce Heritage Trust, 1994.

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Heathcote, Roy. The Rolls-Royce Dart: Pioneering turboprop. Derby, England: Rolls-Royce Heritage Trust, 1992.

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Williams, David E. A view of Ansty, 1935-1982. Derby: Rolls-Royce Heritage Trust, 1998.

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Elliott, Cyril. Fast jets: The history of reheat development at Derby. Derby, Eng: Rolls-Royce Heritage Trust, 2001.

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Ken, Lea, and Rolls-Royce Heritage Trust, eds. Royce and the vibration damper. Derby, England: Rolls-Royce Heritage Trust, 2003.

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Harvey-Bailey, Alec. The Merlin 100 series: The ultimate military development. Derby, England: Rolls-Royce Heritage Trust, 1993.

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Vikings at Waterloo: The wartime work on the Whittle jet engine by the Rover Company. Derby, England: Rolls-Royce Heritage Trust, 1996.

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Harvey-Bailey, Alec. The Merlin in perspective: The combat years. 4th ed. Derby, England: Rolls-Royce Heritage Trust, 1995.

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Book chapters on the topic "Rolls-Royce engines"

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Papastathis, Thomas, Marco Ryll, Stuart Bone, and Svetan Ratchev. "Development of a Reconfigurable Fixture for the Automated Assembly and Disassembly of High Pressure Rotors for Rolls-Royce Aero Engines." In Precision Assembly Technologies and Systems, 283–89. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-11598-1_33.

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"Rolls-Royce Bergen." In Pounder's Marine Diesel Engines, 601–11. Elsevier, 2004. http://dx.doi.org/10.1016/b978-075065846-1/50024-9.

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"Allen (Rolls-Royce)." In Pounder's Marine Diesel Engines, 517–29. Elsevier, 2004. http://dx.doi.org/10.1016/b978-075065846-1/50018-3.

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Woodyard, Doug. "Bergen (Rolls-Royce)." In Pounder's Marine Diesel Engines and Gas Turbines, 615–25. Elsevier, 2009. http://dx.doi.org/10.1016/b978-0-7506-8984-7.00023-0.

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Woodyard, Doug. "Allen (Rolls-Royce)." In Pounder's Marine Diesel Engines and Gas Turbines, 525–29. Elsevier, 2009. http://dx.doi.org/10.1016/b978-0-7506-8984-7.00017-5.

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Latarche, Malcolm. "Rolls-Royce/MTU." In Pounder's Marine Diesel Engines and Gas Turbines, 667–80. Elsevier, 2021. http://dx.doi.org/10.1016/b978-0-08-102748-6.00023-2.

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"Combustion Instability And Its Passive Control: Rolls-Royce Aeroderivative Engine Experience." In Combustion Instabilities In Gas Turbine Engines, 65–88. Reston ,VA: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/5.9781600866807.0065.0088.

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Cantor, Brian. "Griffith’s Equation." In The Equations of Materials, 249–66. Oxford University Press, 2020. http://dx.doi.org/10.1093/oso/9780198851875.003.0012.

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Most materials fracture suddenly because they contain small internal and surface cracks, which propagate under an applied stress. Griffith’s equation shows how fracture strength depends inversely on the square root of the size of the largest crack. It was developed by Alan Griffith, while he was working as an engineer at Royal Aircraft Establishment Farnborough just after the First World War. This chapter examines brittle and ductile fracture, the concepts of fracture toughness, stress intensity factor and stBiographical Memoirs of Fellows ofrain energy release rate, the different fracture modes, and the use of fractography to understand the causes of fracture in broken components. The importance of fracture mechanics was recognised after the Second World War, following the disastrous failures of the Liberty ships from weld cracks, and the Comet airplanes from sharp window corner cracks. Griffith’s father was a larger-than-life buccaneering explorer, poet, journalist and science fiction writer, and Griffith lived an unconventional, peripatetic and impoverished early life. He became a senior engineer working for the UK Ministry of Defence and then Rolls-Royce Aeroengines, famously turning down Whittle’s first proposed jet engine just before the Second World War as unworkable because the engine material would melt, then playing a major role in jet engine development after the war, including engines for the first vertical take-off planes.

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Conference papers on the topic "Rolls-Royce engines"

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Jensen, Daniel, and John Leonard. "Rolls-Royce and Allison Lift Engines." In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5340.

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Wilson, N. J. "Developing the Rolls-Royce Tay." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-302.

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Description & Application The paper traces the evolution of the Tay engine, launched in response to the requirement for an engine suitable for powering a FAR Part 36 Stage 3 noise compliant aircraft in the 70–100 seat range. The engine, which is derived from the Spey (RB183) MK 555 installed in the Fokker F28 aircraft, incorporates several latest technology features a number of which are already in service in large turbofan engines. Modularity and maintainability are key areas which have been addressed in the design of the engine; these are discussed in regard to operation in service. Results, Conclusions & General Observations The eight engine/two year development programme from first engine run to Type Approval by the United Kingdom Civil Aviation Authority is reviewed with detail description of some of the more important and interesting tests. Certification by the US Federal Aviation Administration was subsequently achieved under reciprocal cross-validation procedures. Flight certification of the two lead aircraft applications is now complete. With completion of type certification of the baseline engine and production deliveries now underway, attention is being turned to growth derivative versions of the engine: an uprated version, due to come on stream late 1988 in an increased weight version of the Fokker 100 has now commenced its certification programme — and further growth capabilities are being explored.

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Lock, G. D., M. Child, V. Cheng, R. Johnson, W. Mezzullo, C. Pattinson, S. Peet, and C. Wright. "An Undergraduate Industrial Design Exercise at Rolls-Royce plc." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-90130.

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The Department of Mechanical Engineering at the University of Bath has been conducting an undergraduate engine-related design exercise at Rolls-Royce, Bristol since 2000. Each year a team of six undergraduates complete an engine-related design project under supervision from the company between February and September. This work is coordinated and assessed at both the company and university, and counts overall as 20% of the student’s four-year degree. In addition to working at Rolls-Royce, the students submit reports and give seminars at the university. The design exercise is predominantly technical in nature but must include a significant business element. The students are paid as company employees, typically £7.2k for the six months. This paper describes the design exercise and how it is accommodated into the undergraduate programme of study at the University of Bath. The benefits to the university, the students and the company are discussed. In addition, the six students undertaking the 2005 exercise describe their projects. This year there were three projects, two of which were continuations from previous design exercises. The three projects are listed below. Aero-Engine Rotor-Dynamics (V Cheng and S Peet): An experimental and computation study of engine vibration using a rotor-dynamics rig, simulating the engine. The aim was to assess the accuracy and improve the modeling techniques used at Rolls-Royce. Implementing Design for Environment on Gas turbine engines using a Design Tool (W Mezzulo): A study to create a tool to enable the designer to evaluate the environmental aspects of the life of an engine component. Aero-thermodynamics of aero-engines (M Child, R Johnson and C Pattinson): Various design aspects of aero-engines, both computational and business. Note that M Child’s project is not discussed here for reasons of Rolls-Royce proprietary and confidentiality.

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Russom, Dennis M., and Robert L. Jernoske. "U.S. Navy Rolls-Royce Allison 501-K34 Operating Experience." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0602.

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The Rolls-Royce Allison (RRA) 501-K34 serves as the prime mover for the Ship Service Gas Turbine Generator sets (SSGTGs) of the U.S. Navy’s DDG-51 Class ships. Navy experience with the 501-K34 began in 1988 with the testing of the first prototype. Experience to date includes over 700,000 fired hours on a growing fleet of engines. This paper explores that operating experience and discusses future plans to improve the engine’s operational availability while lowering life cycle costs.

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Russom, Dennis, Jeffrey Patterson, and Ivan Pineiro. "Analysis of U.S. Navy Rolls Royce 501-K34 Turbine Engine Removals 2008 to 2018." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91535.

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Abstract The Rolls Royce 501-K34 gas turbine engine serves as the prime mover in the Ship Service Gas Turbine Generators (SSGTGs) of the U.S Navy’s USS ARLEIGH BURKE (DDG 51) Class Flight I and Flight II ships. At the time of this writing, there are 65 ships and 195 shipboard 501-K34 turbine engines which operate a total of about 400,000 hours per year. Engines periodically require removal from ships for depot repair. This paper discusses the guidelines that govern the removal process then discuss the 156 engine removals that occurred between January 2008 and November 2018.

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Ali, Sy A., and Robert R. Moritz. "Rolls-Royce Power Generation Current Products and New Product Plans." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0393.

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Aero-derivative gas turbines have been successfully serving the power generation, mechanical drive, and marine markets for 40 years. These products are well suited for distributed generation, with sizes in the range from 3 MW to 50+ MW. The Rolls-Royce group of companies provide vertical integration for aero-derivative based energy systems, having marketing, sales, manufacturing, packaging, distribution, and customer service capabilities. The 3– 6 MW, 501-K family serves power generation and cogeneration applications. The new 6–8 MW 601 is used for cogeneration and mechanical drive. The 15 MW Avon is widely applied to mechanical drives, offering exceptional reliability and low life cycle cost. The RB211 provides over 30 MW at high efficiency, and is used in mechanical drive and electrical generation. The 42% efficient, 50 MW, Trent is primarily intended for electrical generation. This engine retains a higher than usual degree of commonality with aero production modules, thus retaining the cost advantage of high volume production and benefits from continuous improvements in aero engines. Plans: Cost reduction of mature existing products will be achieved by “industrialization”, e.g. by alloy changes and shape simplification, of parts no longer in aero production. Better integrated packaging and “more electric aircraft” features are rapidly becoming a necessity in the competitive marketplace. The trend is toward minimizing and possibly eliminating mechanical drives and other components in a gas turbine to improve product quality, efficiency, reduce product cost, while enhancing product quality and the environment. In this regard, the approach being taken near term is to substitute normal oil bearings with Active Magnetic Bearings. Such an action would help eliminate high cost skid lubrication system components and some environmental hazards as well as reducing maintenance. Several programs will make contributions to environmental improvements through reduced emissions and the use of “renewable” fuels. A prototype 501-K has been supplied to operate on gasified coal, a reduced emissions path to generating electricity from coal. A dual fuel DLE combustion system for very high pressure ratio and turbine temperature is in development for the Trent, having downward compatibility with other company products. The Next Generation Gas Turbine (NGGT) project, sponsored by the US Department of Energy, will use an existing engine core. Advanced modules, including a long life “spiral” recuperator and cycle enhancements combine to yield 50% cycle efficiency at a reduced cost per kW. The goal is to produce a 50 MW class plant with “combined cycle efficiency at simple cycle cost.” The NGGT is suited to using alternate fuel for part of the energy input. Following evaluation of fuel cell/gas turbine hybrids, a specially suited gas turbine development is being initiated with sponsorship by the U.S. Department of Energy. The company is also conducting a solid oxide fuel cell program. An auxiliary power unit(APU) was developed and is now in production for the M1 tank. A “microturbine” derivative of this product is being considered for distributed generation.

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Lazik, W., Th Doerr, S. Bake, R. v. d. Bank, and L. Rackwitz. "Development of Lean-Burn Low-NOx Combustion Technology at Rolls-Royce Deutschland." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51115.

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Lean-burn combustion technology is identified to be the key technology for aero-engine combustion systems to achieve future legislative requirements for NOx. The lean-burn low NOx combustor development at Rolls-Royce Deutschland RRD for the upcoming generation of aero-engines is presented, which has been supported by the German aeronautical research programme. The down selection process of different injector concepts is described in detail to develop lean-burn fuel injection technology up to a technology level for engine application. Initial concept validation with testing on single sector combustion rigs applying advanced laser measurement techniques is followed by high power single sector emission tests to prove low emission characteristics. Climbing the level of technology readiness, which is in each phase substantiated by intense CFD simulations, the most promising low emissions design concepts have been investigated for unrestricted combustor operability compared to conventional rich burn systems. Altitude relight, weak extinction margins, fuel staging optimisation and combustion efficiency in the vicinity of staging points have been optimised on different sub-atmospheric, atmospheric, medium and high-pressure test vehicles. The validation process concludes with sub-atmospheric and high-pressure testing within a fully annular test environment before the final lean-burn fuel injector configuration has been selected for core engine testing to prove emission performance and operability of the fuel-staged combustion system. Two fuel injector configurations were successfully tested in a high-pressure fully annular rig. The combustor module and both injector standards have been cleared for core engine operation.

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Bonafede, Americo, Dennis Russom, and Matthew Driscoll. "Common Threads for Marine Gas Turbine Engines in U.S. Navy Applications." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-28217.

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This paper discusses the common threads that have been gleaned by the Navy in having operated many different gas turbine engines in a marine environment for nearly thirty years. The status of the Navy’s Honeywell TF40B, Rolls Royce 501 and General Electric LM2500 gas turbine engine programs is discussed.

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Caguiat, Daniel E., David M. Zipkin, and Jeffrey S. Patterson. "Rolls Royce/Allison 501-K Gas Turbine: Anti-Fouling Compressor Coatings Shipboard — Phase I." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38739.

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Naval Surface Warfare Center Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 conducted a land-based evaluation of fouling-resistant compressor coatings for the 501-K17 Ship Service Gas Turbine Generator (SSGTG) [1]. The purpose of this evaluation was to determine whether such coatings could be used to decrease the rate of compressor fouling and associated fuel consumption. Based upon favorable results from the land-based evaluation, a similar coated compressor gas turbine engine was installed onboard a United States Navy vessel. Two data acquisition computer (DAC) systems and additional sensors necessary to monitor and compare both the coated test engine and an uncoated control engine were added. The goal of this shipboard evaluation was to verify land-based results in a shipboard environment. Upon completion of the DAC installation, the two gas turbine engines were operated and initial data was stored. Shipboard data was compared to land-based data to verify validity and initial compressor performance. The shipboard evaluation is scheduled for completion in June 2003, at which time data will be analyzed and results published.

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Vega, Jesús, Edison E. Torres Garcia, Oscar G. Verdugo, and Luisa F. Monico Muñoz. "Prevention of Compressor Stall on Rolls Royce M250 Engines C20 Series Using Trend Monitoring Analysis." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1352.

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