An Undergraduate Industrial Design Exercise at Rolls-Royce plc

2006 ◽  
Author(s):  
G. D. Lock ◽  
M. Child ◽  
V. Cheng ◽  
R. Johnson ◽  
W. Mezzullo ◽  
...  
Keyword(s):  
Rotor Dynamics ◽  
Design Tool ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Vibration ◽  
Previous Design ◽  
Undergraduate Programme ◽  
Aero Engines ◽  
The University ◽  
Related Design

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.

Analysis of Material Coating for Damping in Beam Structures

2010 ◽  
Vol 442 ◽  
pp. 202-210
Author(s):  
S.H. Raza ◽  
M.A. Malik ◽  
W. Akram
Keyword(s):  
Turbine Blades ◽  
Beam Theory ◽  
Industrial Applications ◽  
Theory Model ◽  
Design Tool ◽  
Coating Material ◽  
Mode Shapes ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Finite Element Procedure

Vibratory stresses are the main cause of material failure in aerospace/mechanical structures and machine components. Failure also occurs due to these vibratory stresses in gas turbine engines and rotating machinery components while operating at resonant frequency. A magnetomechanical coating material is used as a very effective method for damping of these stresses. Vibratory stress damping in components like turbine blades through magnetomechanical coating material is well known in literature. However, the geometric correlations for the varying coated beam are not well established. We have utilized a cantilever beam as the basic geometry for this investigation to establish a correlation for varying coating. Beam theory is applied as a mathematical model for obtaining the mode shapes for the beam. A finite element procedure is performed to acquire the data and this data is then correlated with beam theory model for initial verification. This data is further evaluated to form the required model for calculating thickness of coating for a beam. The resulting parametric correlation is verified through comparison with the already published experimental data available in literature. This correlation can be used as a design tool for suppression of vibratory stresses in industrial applications.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

1990 ◽  
Author(s):  
Yoshiharu Tsujikawa ◽  
Makoto Nagaoka
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Specific Impulse ◽  
Optimization Procedure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Scramjet Engine ◽  
Aero Engines

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.

USNS LCPL Roy M. Wheat: Zorya DT-59 Gas Turbine Installation and Integration

2004 ◽  
Author(s):  
Richard DeCorso ◽  
Daniel E. Caguiat ◽  
Jeffrey S. Patterson ◽  
David M. Zipkin
Keyword(s):  
Gas Turbine ◽  
Engine Speed ◽  
Vibration Monitoring ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Engine Vibration ◽  
Video Record ◽  
Protection Circuits ◽  
Turbine Installation ◽  
The U.S

In June 1997, the U.S. Navy purchased the Soviet military cargo ship “Vladimir Vaslyaev” for conversion to the USNS LCPL Roy M. Wheat for use in the Maritime Prepositioning Force. This paper documents the efforts of NSWCCD and dB Associates in supporting the installation, startup, and integration of the ship’s controls with the two Zorya DT-59 main propulsion gas turbine engines (GTE’s). The installation documentation developed included a video record of the port and starboard gas turbine installations, as well as information that aided in the development of the Engineering Operational Procedures (EOP). The integration for the DT-59s focused on providing engine speed sensors, an engine vibration monitoring system and engine reversing protection circuits.

A Framework for Novelty Detection in Jet Engine Vibration Data

2007 ◽  
Vol 347 ◽  
pp. 305-310 ◽  
Author(s):  
David A. Clifton ◽  
Peter R. Bannister ◽  
Lionel Tarassenko
Keyword(s):  
Novelty Detection ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Analysis Framework ◽  
Vibration Data ◽  
Engine Vibration ◽  
Detection Approach ◽  
On Line ◽  
High Integrity ◽  
Line Analysis

A novelty detection approach to condition monitoring of aerospace gas-turbine engines is presented, providing a consistent framework for on- and off-line analysis, each with differing typical implementation constraints. On-line techniques are introduced for observing abnormality in engine behaviour during aircraft flights, and are shown to provide early warning of engine events in real-time. Off-line techniques within the same analysis framework are shown to allow the tracking of single engines and fleets of engines from ground-based monitoring stations on a flight-by-flight basis. Results are validated by comparison to conventional techniques, in application to aerospace engines and other industrial high-integrity systems.

scholarly journals Royal Navy Experience of Propulsion Gas Turbines and How and Why This Experience is Being Incorporated Into Future Designs

1999 ◽  
Author(s):  
James Rand ◽  
Nigel Wright
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Electric Propulsion ◽  
High Speed ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Royal Navy ◽  
Electric Ship ◽  
Prime Movers ◽  
Aero Engines

The Royal Navy (RN) has in-service experience of both marinised industrial and aero derivative propulsion gas turbines since the late 1940’s. Operating through a Memorandum of Understanding (MOU) between the British, Dutch, French and Belgian Navies the current in-service propulsion engines are marinised versions of the Rolls Royce Tyne, Olympus and Spey aero engines. Future gas turbine engines, for the Royal Navy, are expected to be the WR21 (24.5 MW), a 5 to 8 MW engine and a 1 to 2 MW engine in support of the All Electric Ship Project. This paper will detail why the Royal Navy chose gas turbines as prime movers for warships and how Original Equipment Manufacturers (OEM) guidance has been evaluated and developed in order to extend engine life. It will examine how the fleet of engines has historically been provisioned for and how a modular engine concept has allowed less support provisioning. The paper will detail the planned utilisation of advanced cycle gas turbines with their inherent higher thermal efficiency and environmental compliance and the case for all electric propulsion utilising high speed gas turbine alternators. It will examine the need for greater reliability / availability allowing single generator operation at sea and how by using a family of 3 engines a nearly flat Specific Fuel Consumption (SFC) down to harbour loads can be achieved.

Systematic Evaluation of U.S. Navy LM2500 Gas Turbine Condition

2002 ◽  
Vol 124 (3) ◽  
pp. 580-585 ◽  
Author(s):  
B. D. Thompson ◽  
B. Wainscott
Keyword(s):  
Gas Turbine ◽  
Systematic Evaluation ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Short Term ◽  
Engine Vibration ◽  
Mechanical Faults ◽  
System Data ◽  
Short And Long Term

From an operational availability stand point, the U.S. Navy is interested in the short term reliability of its ship based LM2500 gas turbine engines. That is the likelihood that an engine will operate successfully through a six-month deployment (usually 1500 to 2000 operational hours). From a maintenance and cost of ownership standpoint both the short-term and long-term reliability are of concern. Long-term reliability is a measure in time (in operating hours) between engine removals. To address these requirements U.S. Navy Fleet support maintenance activities employ a system of tests and evaluations to determine the likelihood that an LM2500 will meet its short and long-term goals. The lowest level inspection is the predeployment inspection, which attempts to identify primarily mechanical faults with the engine. Gas Turbine Bulletin inspections are used to determine if predefined wear out modes exists. Performance evaluations can be performed which determine the ability of the LM2500 and its control system to meet expected power requirements. Lube oil system data can be analyzed to determine if excessive leakage or excessive scavenge temperatures exist. Engine vibration characteristics can be reviewed to identify the source of both synchronous and nonsynchronous vibration and determine if corrective measures need to be taken. This paper will discuss how the lowest level inspections feed the more sophisticated analysis and how these inspections and evaluations work to provide a systematic method of insuring both short and long-term LM2500 reliability.

Royal Navy Experience of Propulsion Gas Turbines and How and Why This Experience is Being Incorporated Into Future Designs

2000 ◽  
Vol 122 (4) ◽  
pp. 680-684 ◽  
Author(s):  
James Rand ◽  
Nigel Wright
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Electric Propulsion ◽  
High Speed ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Royal Navy ◽  
Electric Ship ◽  
Prime Movers ◽  
Aero Engines

The Royal Navy (RN) has in-service experience of both marinized industrial and aero derivative propulsion gas turbines since the late 1940s. Operating through a Memorandum of Understanding (MOU) between the British, Dutch, French, and Belgian Navies the current in-service propulsion engines are marinized versions of the Rolls Royce Tyne, Olympus, and Spey aero engines. Future gas turbine engines, for the Royal Navy, are expected to be the WR21 (24.5 MW), a 5 to 8 MW engine and a 1 to 2 MW engine in support of the All Electric Ship Project. This paper will detail why the Royal Navy chose gas turbines as prime movers for warships and how Original Equipment Manufacturers (OEM) guidance has been evaluated and developed in order to extend engine life. It will examine how the fleet of engines has historically been provisioned for and how a modular engine concept has allowed less support provisioning. The paper will detail the planned utilization of advanced cycle gas turbines with their inherent higher thermal efficiency and environmental compliance and the case for all electric propulsion utilizing high speed gas turbine alternators. It will examine the need for greater reliability/availability allowing single generator operation at sea and how by using a family of 3 engines a nearly flat Specific Fuel Consumption (SFC) down to harbour loads can be achieved. [S0742-4795(00)01203-5]

Some Investigations in the Field of Blade Engineering

1958 ◽  
Vol 62 (573) ◽  
pp. 633-646 ◽  
Author(s):  
B. D. Blackwell
Keyword(s):  
Gas Turbine ◽  
Military Service ◽  
Turbine Engines ◽  
Development Phase ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The Past ◽  
Pass Through ◽  
Aero Engines ◽  
New Phase

The past ten years have seen a wide variety of axial gas turbine aero-engines pass through their development phase into military service. A new phase began when the first axial gas turbine engines to operate to a civil schedule entered service in 1956-7, powering the Britannia and Tu.104 aircraft. The coming years will see an ever-increasing percentage of the world’s air traffic being carried by axial gas turbine engines and it may be confidently predicted that in another ten years they will be the rule rather than the exception.The enormous importance of reliability in civil operation is well known. Possibly less well known is the incredibly rapid build-up of running hours which occurs when an engine is introduced into civil operation. In six months of civil operation these may exceed the cumulative hours in the whole life of a military type, and will outstrip the total manufacturers’ bench experience in an even shorter time. With all the achievements in bench development and military service in the past ten years, the axial gas turbine engine is still in the “ kindergarten ” in relation to civil operation.

Evaluation of aero gas turbine preliminary weight estimation methods

2014 ◽  
Vol 118 (1204) ◽  
pp. 625-641 ◽  
Author(s):  
P. Lolis ◽  
P. Giannakakis ◽  
V. Sethi ◽  
A. J. B. Jackson ◽  
P. Pilidis
Keyword(s):  
Gas Turbine ◽  
Estimation Methods ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Weight Estimation ◽  
Turbine Engine ◽  
The Public ◽  
Conceptual Design Phase ◽  
Aero Engines ◽  
Environmental Risk Analysis

AbstractThe estimation of gas turbine engine weight during the preliminary or conceptual design phase is a key part of a Techno-economic Environmental Risk Analysis (TERA). Several methods that are available in the public domain are analysed and compared, in order to establish the physics driving them and their suitability for the weight estimation of modern gas turbine engines. Among the tested methods, only WATE managed to achieve acceptable accuracy for engine optimisation studies. This work demonstrates that the age and restrictions of existing ‘whole engine based’ methods, along with their dependency on old engine databases make them unsuitable for future and novel aero engines. A hybrid weight modelling approach is proposed as a solution permitting the creation of simple ‘whole engine based’ methods that do not depend on the availability of existing engine data, which are also subject to uncertainties and incoherencies.

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