Steve Morris, Facility Manager

Slides:



Advertisements
Similar presentations
Infrastructures in Energy- 10 years experience –how does this feed into the future? Nick Syred Cardiff University.
Advertisements

Finite Element Modeling and Simulation of the Effect of Water Injection on Gas Turbine Combustor NO x Emissions and Component Temperature Joseph M. Basile.
Copyright © 2011 by Oxford University Press, Inc. Energy and the Environment James A. Fay / Dan S. Golomb FIGURE 3.4 The Otto cycle comprises two isentropic.
PACCON 2013 PREDICTION OF NITROGEN OXIDE GENERATED FROM GAS TURBINE ENGINE Global Chemical Sciences for Green Community NATCHANON CHAIPRASERT / AMORNCHAI.
EGR 334 Thermodynamics Chapter 9: Sections 7-8
Introduction of jet engine
Gas Power Cycle - Jet Propulsion Technology, A Case Study
Technology overview 18/03/ /01 PPT.
School of Aerospace Engineering MITE MITE PROGRAM OVERVIEW AND ACCOMPLISHMENTS (MITE-Multidisciplinary University Research Initiative on Intelligent Turbine.
Analysis of Turbo Combustor P M V Subbarao Professor Mechanical Engineering Department A Device to Anchor the Flame…. The Cause of Major component of.
AERONET 2 - workshop “Measurement Technology” - cluster LECT Vienne 19/20 Sept Technical Univ. O. Penanhoat - Snecma Page 1 ENSMA - Optical measurements.
AKA how Mr. R and Ms. Harrington spent their summer.
TURBINE COOLER MAJOR ASSY TURBINE DISC TURBINE DISC IS PART OF THE TURBO COOLER WHICH REDUCES THE TEMPERATURE OF HOT AIR FROM 90±5ºC TO 2ºC.
BTZ-Feb. 16, 2000 MITE NASA Glenn/Army Visitors February 16, 2000 MITE PROGRAM OVERVIEW MURI (Multidisciplinary University Research Initiative) on Intelligent.
JET ENGINE INTERNAL COOLING AND SEALING PREVENTING BURN OUT OF THE HOT SECTION.
 FAN  COMPRESSOR  COMBUSTOR  TURBINE  MIXER  NOZZLE.
Combustor modeling Webinar
PREVENTING BURN OUT OF THE HOT SECTION
Date of download: 6/2/2016 Copyright © ASME. All rights reserved. From: Numerical Investigation of Combustion Instability in a V-Gutter Stabilized Combustor.
Specific, Baglan Bay Innovation and Knowledge Centre, Baglan, Port Talbot, SA12 7AX SPECIFIC IKC – ‘Buildings as Power Stations’ Paul Jones Industrial.
Date of download: 6/26/2016 Copyright © ASME. All rights reserved. From: A Methodology for On the Fly Acoustic Characterization of the Feeding Line Impedances.
Des. Ton Nguyen. MAIN PARTS  Fan  Compressor  Combustor  Turbine  Nozzle.
Date of download: 9/17/2016 Copyright © ASME. All rights reserved. From: The Efficiencies of Internal Reforming Molten Carbonate Fuel Cell Fueled by Natural.
Date of download: 9/20/2016 Copyright © ASME. All rights reserved. From: Laminar Flame Speed and Ignition Delay Time Data for the Kinetic Modeling of Hydrogen.
4 Starting Tips to Keep Your Car in Top Condition
Gas Turbine Engine – Turbojet
Date of download: 10/3/2017 Copyright © ASME. All rights reserved.
Date of download: 10/3/2017 Copyright © ASME. All rights reserved.
CONVERSION OF DIESEL ENGINE INTO DUAL FUEL ENGINE
7–12 ISENTROPIC EFFICIENCIES OF STEADY-FLOW DEVICES
Date of download: 10/18/2017 Copyright © ASME. All rights reserved.
Date of download: 10/19/2017 Copyright © ASME. All rights reserved.
Date of download: 10/20/2017 Copyright © ASME. All rights reserved.
TURBO POWER Turbine Technology
Date of download: 10/22/2017 Copyright © ASME. All rights reserved.
CACTUS MOON EDUCATION, LLC
Date of download: 10/27/2017 Copyright © ASME. All rights reserved.
Date of download: 10/29/2017 Copyright © ASME. All rights reserved.
Date of download: 10/31/2017 Copyright © ASME. All rights reserved.
Date of download: 11/6/2017 Copyright © ASME. All rights reserved.
Generic Swirl Burner At the moment some 20% of the world’s (50% in Wales) total electricity supply is derived from GT based systems primarily fired on.
Date of download: 11/13/2017 Copyright © ASME. All rights reserved.
Power Plant Technology Combined Cycle and Renewable Energy Power Systems (Assignment 1) by Mohamad Firdaus Basrawi, Dr. (Eng) Mechanical Engineering Faculty.
Date of download: 12/29/2017 Copyright © ASME. All rights reserved.
Date of download: 12/31/2017 Copyright © ASME. All rights reserved.
Date of download: 12/31/2017 Copyright © ASME. All rights reserved.
Jie WANG;Zuohua HUANG ;Bing LIU;Xibin WANG;
Power Plant Technology Steam and Gas Cycle Power Plant (Assignment 2)
GAS TURBINE POWER PLANT
Dual Fuel Engines.
Engineering Thermodynamics ME-103
MAE 5360: Hypersonic Airbreathing Engines
Furnace Heat Transfer & Steam Generation
Basic Design Principles of Turbofan Engine
Alien life on Mars – caught in crystals?
“V” MACHINE PROBLEMS & SOLUTIONS
Chain Wear QI Plots Data from Testkeys , , , , and
Performance Analysis of Ramjet Engines
Ch. 10 Heat Transfer in Engines
EGR and Air Injection Systems
ASME Turbo Expo Montreal May 14-17, 2007
Study of Hydrogen/Syngas Combustion and NO Emissions at High Pressures and Temperatures Yiguang Ju, Department of Mechanical and Aerospace Engineering,
Les Shirvill1, Mark Royle2 and Terry Roberts2 1Shell Global Solutions
PAL 4/27/12 Air at 7oC enters a turbojet engine at a rate of 16 kg/s and a velocity of 300 m/s (relative to the engine). The air is heated in the combustion.
Chapter 3 Section 3 The behavior of Gases.
ENERGY CONVERSION ES 832a Eric Savory
Combustion in S.I. Engine
Steve Morris, Facility Manager
Steve Morris, Facility Manager
Advanced Vaporization System for Small Jet Engines
Presentation transcript:

Steve Morris, Facility Manager Gas Turbine Research Centre (GTRC) Heol Cefn Gwrgan Road Margam Port Talbot, UK SA13 2EZ Tel: ++ 44 (0) 1639 864751 e-mail:morrissm@cf.ac.uk Web: www.cu-gtrc.co.uk

High Pressure Combustor Rig (HPCR) Inlet air pressure 16 bara Inlet air temperature 900K Inlet air flow 5 kg/s

Inlet air pressure 16 bara Inlet air temperature 900K HPCR Test Modules Combustion Instability rig Auto-ignition rig Wall cooling rig UPGRADE: Optical Combustor Inlet air pressure 16 bara Inlet air temperature 900K Inlet air flow 5 kg/s

HPCR Test Modules Hot End Simulator