Spelling suggestions: "subject:"gas turbine engine""
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Investigations of a diesel gas turbineParkin, R. January 1980 (has links)
No description available.
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Influence of subsonic aero engine design and flight routes on atmospheric pollutionLe Dilosquer, Marc January 1998 (has links)
Gas turbine engine NOX, CO2 and H20 exhaust emissions from civil subsonic fleets are potentially in sufficient amounts to affect atmospheric ozone and climate, particularly with the projected growth in air traffic. Because, it may be that the future envisaged low-NOX combustor technologies may not keep up with the industry requirements for increased engine thermal efficiency, the potential benefits from optimising aero engine cycles and flight operations for low mission emissions deserve to be thoroughly investigated. The SKY computer simulation system developed to examine such alternative routes integrates flight route performance, aero engine performance and the formation of pollutants within the combustor. Based on Turbomatch, Cranfield Gas Turbine Simulation System, SKY can be used to optimise mission/aircraft/engine/combustor combinations with respect to landing and take-off (LTO) as well as mission emissions. A model of the high capacity Boeing 747-400 powered by Turbomatch high bypass ratio turbofan models and simulated on long range routes such as London-Tokyo is selected for this work. On the one hand, aero engine cycles can be designed at a optimum bypass ratio and deliver mission NOX reductions of up to 10% over designs optimised for LTO NOX, indicating that the current ICAO regulatory regime is a inadequate parameter to control mission NOX. On the other hand, operational measures such as speed reductions could bring further reductions of the order of 10%, but some of the improvement would be made at the expense of fuel burn, CO2 and H20 emissions, payload-range capability and direct operating costs. The benefits from such alternative routes are not negligible but smaller in comparison to the 30 to 80% potential cuts from future low-NOX technology, as well as to the 30% reduction due to expected improvements in the next 20 years or so in airframe weight and aerodynamics and more efficient navigation practices.
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Secondary flows and losses in gas turbinesGraves, C. P. January 1985 (has links)
Early stages of axial flow turbine design require a relatively simple prediction technique for estimating both blade row exit angle and loss profiles produced by secondary flows. Detailed experimental investigation of the flow field in a large scale linear cascade of high turning turbine rotor blades has been made. This gave improved understanding of cascade secondary flow phenomena. and a physical basis for secondary flow angle and loss predictions. Data suitable for comparison with three dimensional flow calculations is presented. Experimental data was obtained utilizing cobra probes throughout the flow field. and hot wire probes at cascade inlet and exit. Results are presented graphically on various planes through the flow field using both contour and vector plots. The developing passage and leading edge horseshoe vortic 3S are traced. and their interactions with the cascade inlet boundary layer are clearly visible. At cascade exit two major secondary loss components were identified: a loss core shed from the suction surface formed largely of inlet boundary layer fluid. and an area consisting of new endwall boundary layer fluid swept towards the suction surface. Highly turbulent flows were also evident close to these regions. Secondary losses were predicted using three discrete loss components: the loss core. a non skewed new endwall boundary layer. and an extra secondary loss related to the classical secondary flow kinetic energy. Experimental data from several sources was compared with secondary loss predictions with some success. Some modifications are clearly desirable to enhance the loss prediction technique. but the relatively simple method gives encouraging results.
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A numerical study into the heat transfer beneath the stator blade of an axial compressorRayner, D. January 1992 (has links)
No description available.
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Aero engine life evaluated for combined creep and fatigue, and extended by trading-off excess thrustWu, Fuh-Eau January 1994 (has links)
This thesis investigates the concept of thrust rating as a means towards reducing the life cycle costs of engine ownership. Towards this end, this thesis has discussed the concept of thrust rating, developed computer programs for mechanical load type failures, which include creep, LCF, and combinations thereof, and conducted simulations of improving life usage and reducing life cycle costs. A study was performed on a military engine, under an original design mission mix, that showed significant gains in creep-LCF life of the HPT blade could be achieved, especially With the recently proposed and presumably more accurate criterion- ductility exhaustion, by thrust rating. The savings were expressed in terms of an approximate reduced life accumulation rates and life cycle costs. The net result was a 50% increase in creep-LCF life with a savings of $50.4 million. These calculations were based on a Feet of 300 engines having the designed lifetime of 8,000 operating hours per engine. Throughout the thesis, mention is also made of employing the thrust rating concept on other engines. To this end, the thesis will also give a blueprint for conducting a feasibility study to employ thrust rating as a maintenance tool. In addition to the technical aspects, the role of maintenance and aircraft operations policy will also be studied to determine the interrelationships that exist between thrust rating technology and its practical application.
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Stall and surge in axial flow compressorsWilson, Alexander George January 1996 (has links)
The objective of the work described in this thesis is twofold; to elucidate the nature of stall and surge in an axial flow aeroengine compressor, and to improve on current computational stall modelling techniques. Particular attention is paid to the initial stages of the stall/surge transient, and to the possibility of using active control techniques to prevent or delay the onset of stall/surge. A detailed analysis is presented of measurements of the stalling behaviour of a Rolls- Royce VIPER jet engine, showing a wide variety of stall inception and post-stall behaviour. Stall transients are traced from disturbances through to stable rotating stall or axisymmetic surge. The stall inception pattern at nearly all speeds is shown to conform to the short circumferential length scale pattern described by Day [1993a]. A multiple compressors in parallel stall model is developed using conventional stall modelling techniques, but extended to include the effects of the jet engine environment The model is shown to give a good representation of the overall stalling behaviour of the engine, although the details of the stall inception period are not accurately predicted. A system identification technique is applied to the results of the model in order to develop a method of active control of stall/surge. A new stall model is introduced and developed, based on a time-accurate three dimensional (but pitchwise averaged) solution of the viscous flow equations, with bladerow performance represented by body forces. The flow in the annulus boundary layers is calculated directly, and hence this new method is sufficiently complex to model the initial localised disturbances that lead to stall/surge. At the same time the computational power required is compatible with application to long multistage compressors.
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Variable geometry turbocharging of transport diesel enginesBaghery, A. January 1982 (has links)
A boost controlled continuously variable geometry turbocharger prototype has been designed, manufactured and tested. The prototype has been first rig tested and later fitted to a Perkins T6.354 diesel engine. The engine tests have included both steady state and transient runs. Torque back up has been improved considerably increasing from 34.3% to 55.8%, the former occurring at 1400rpm while the latter at 1200rpm. In the experimental programme, compressor surge has been the limiting parameter while in the theoretical investigations a wide mass flow compressor has been assumed and the limiting parameter was maximum cylinder pressure. In the theoretical investigations lower compression ratio and retarded injection timing have been considered to further improve the scope for higher torque back up and improved transient response. In addition the performance of the variable geometry turbocharged engine using a simple boost controlled turbine restriction schedule has been simulated. It is concluded that a simple boost controlled system will present sfc penalties in the part load regime and thus more sophisticated multi-variable schemes will have to be studied if sfc optimization is to be achieved. The experimental programme has been conducted using the 'zip fastener' design. This design has been found to be strongly non-linear with respect to turn down ratio in response to turbine restriction but will offer the required effects at the expense of a slight drop in turbine efficiency. However, in future investigations initial calibration studies have to be undertaken to ensure comparable swallowing capacities with the standard turbine which the variable geometry turbine replaces.
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A study into vibrations of turbocharger blading with a lacing wireWang, Xu January 1994 (has links)
The vibration of a turbocharger blade and dynamic characteristics of bladed packets connected by a lacing wire have been studied. The study was carried out using three analytical and experimental methods. They are: Modal Testing, Electronic Speckle Pattern Interferometry (ESPD and Finite Element Analysis (FEA)). Vibration modes of a turbocharger blade with aerodynamic profile, with and without a lacing wire, were identified using model blades with simplified geometry. The separation of coupled modes was achieved using ESPI tests. The modes of vibrations of bladed packets were identified. The effect of inter-blade coupling through a lacing wire is that a cluster of sub-modes are generated in bladed packets corresponding to each fundamental mode of the freestanding blade, the number of the sub-modes being equal to the number of blades in the packet. Apart from the fundamental sub-mode, the vibration of all other submodes are out of phase with different phase relations. The stiffness of the lacing wire and its location with respect to the blade make great contributions towards certain mode clusters in terms of mode shapes and natural frequencies. The nonlinearity of the stiffness of the deformed lacing wire caused by centrifugal force was established. The coupling of this non linearity with different vibration amplitudes, due to different phase relation, results in the dynamic mistuning in lacing wire stiffness. This mistuning is considered to be a major attribute in reducing the responses at resonance.
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Convective heat transfer to gas turbine bladesRoberts, G. January 1983 (has links)
This thesis initially describes the experimental work which was carried out in order to examine the effects of parameters such as the blade profile, free stream turbulence intensity etc. on the onset and, extent of transition in the boundary layer on a turbine blade. A series of four different blade profiles with identical pressure surfaces but different suction surfaces, were tested. The suction surfaces differed in the severity and extent of their initial favourable pressure gradients. Tests were carried out for a range of throat Mach numbers and free stream turbulence intensities. From the results obtained it is suggested that the most significant factor is 'the severity of the initial. favourable pressure gradient. This appears to have an inhibiting effect on the influence of the free stream turbulence and on the growth of the turbulent stresses in the transition region. Using these hypotheses, modifications were made to an existing boundary layer prediction program in order to provide a better transition-model and to include the effect of free stream turbulence.
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Σχεδιασμός στοιχείων κατασκευών από σύνθετα κεραμικά υλικά που λειτουργούν υπό συνθήκες θερμομηχανικής κόπωσηςΒλάχος, Δημήτριος Ε. 05 March 2009 (has links)
Αρκετές φορές υπήρξαν επιστημονικές ανακαλύψεις που περίμεναν την δημιουργία νέων ή την
βελτίωση γνωστών υλικών, προτού βρούν εφαρμογή. Σε άλλες περιπτώσεις πάλι, καινοτομίες στην
τεχνολογία των υλικών υπήρξαν το κίνητρο για την ανάπτυξη νέων εφαρμογών και εφευρέσεων. Είναι
πράγματι εντυπωσιακό το πόσα από τα σύγχρονα τεχνολογικά επιτεύγματα οφείλουν την ύπαρξή τους
στην, τυχαία πολλές φορές, ανακάλυψη ενός πρωτοποριακού υλικού, μιας νέας μεθόδου επεξεργασίας,
ή άγνωστων ιδιοτήτων σε γνώριμα υλικά.
Σήμερα ο τομέας των υλικών αποτελεί ανεξάρτητο πεδίο επιστημονικής έρευνας με έντονη
δραστηριότητα. Παράλληλα επιτελείται σημαντικό έργο με στόχο την αξιοποίηση από την τεχνολογία,
των ερευνητικών αποτελεσμάτων της επιστήμης των υλικών. Μία άποψη της δραστηριότητας αυτής
είναι η εισαγωγή σε πειραματικό επίπεδο, νέων υλικών σε γνωστές εφαρμογές. Αν και αυτό αποτελεί
ένα σημαντικό βήμα, ωστόσο η υιοθέτηση ενός υλικού από την βιομηχανία με την είσοδό του στην
παραγωγή, εξαρτάται από πολλούς παράγοντες. Ένας από τους πιο καθοριστικούς, ειδικά όσο αφορά
εφαρμογές υψηλής τεχνολογίας, είναι η δυνατότητα προσαρμογής των διαδικασιών σχεδιασμού στις
συνθήκες που διαμορφώνονται από τα ιδιαίτερα χαρακτηριστικά της συμπεριφοράς του υλικού, σε
συνδυασμό με τις απαιτήσεις της εφαρμογής.
Σε αυτό το γενικό πλαίσιο εντάσεται η παρούσα εργασία, η οποία έχει ως αντικείμενο την ανάπτυξη
μεθοδολογίας σχεδιασμού, κατάλληλης για εφαρμογή σε στοιχεία από Σύνθετα Κεραμικά Υλικά
Συνεχών Ινών (Continuous Fiber Ceramic Composites – CFCC’s) καταπονούμενα από θερμομηχανικά
φορτία. Τα ΣΚΥ Συνεχών Ινών αποτελούν εξελιγμένη μορφή των Προηγμένων Κεραμικών Υλικών, τα
οποία είναι ίσως τα πλέον ανθεκτικά υλικά σε περιβάλλοντα υψηλών θερμοκρασιών που έχουν
αναπτυχθεί έως σήμερα. Τα ΣΚΥ είναι αντικείμενο συνεχούς έρευνας και ανάπτυξης και αναμένεται να
επιφέρουν σημαντική πρόοδο σε πολλούς τομείς. Μία από τις πολλές εφαρμογές για τις οποίες
θεωρούνται ελκυστικά, είναι οι στροβιλοκινητήρες αεροχημάτων και οι στροβιλομηχανές παραγωγής
ενέργειας. Η αντικατάσταση των μεταλλικών κραμμάτων από ΣΚΥ στα «θερμά» μέρη των
στροβιλομηχανών εκτιμάται ότι είναι δυνατό να επιφέρει αύξηση του βαθμού απόδοσης έως και 20% με
ταυτόχρονη μείωση των εκπεμπόμενων ρύπων. Στην περιοχή αυτή εστιάζεται η παρουσίαση της
προτεινόμενης μεθοδολογίας και συγκεκριμένα στον σχεδιασμό και την ανάλυση ενός πρότυπου
θαλάμου καύσης στροβιλομηχανής κατασκευασμένου από ΣΚΥ. Η μεθοδολογία αυτή επιχειρεί να
καλύψει τις ιδιαίτερες απαιτήσεις της μοντελοποίησης των ΣΚΥ και της ανάλυσης στοιχείων
κατασκευών από ΣΚΥ, που προκύπτουν από τα χαρακτηριστικά της συμπεριφοράς τους στις συνθήκες
λειτουργίας των στροβιλομηχανών.
Ως βασικό στοιχείο της μεθοδολογίας σχεδιασμού συμπεριλαμβάνεται στην παρούσα εργασία και η
λεπτομερής περιγραφή του πειραματικού χαρακτηρισμού ενός τύπου ΣΚΥ με μήτρα και ενίσχυση
οξειδίων. Στην διαδικασία αυτή εισάγεται και μια πρωτότυπη μέθοδος ποσοτικού χαρακτηρισμού που
στηρίζεται σε μη-καταστροφικές δοκιμές με χρήση υπερήχων. Η διαδικασία εφαρμογής της μεθόδου,
όσο αφορά το πειραματικό και το υπολογιστικό μέρος της αναπτύχθηκε εξ’ολοκλήρου στα πλαίσια της
παρούσας εργασίας και επιτρέπει την ανίχνευση και τον ποσοτικό προσδιορισμό ανισότροπης βλάβης
σε ΣΚΥ. Η επεξεργασία των αποτελεσμάτων της διαδικασίας χαρακτηρισμού, οδηγεί στην διαμόρφωση
μαθηματικού μοντέλου που περιγράφει την μηχανική συμπεριφορά του υλικού κάτω από δεδομένες
συνθήκες λειτουργίας. Συγκεκριμένα, όσο αφορά τα ΣΚΥ με μήτρα και ενίσχυση από οξείδιο του
αλουμινίου στα οποία εστιάζεται η εργασία, διαπιστώθηκε υποβάθμιση των ελαστικών ιδιοτήτων και
της αντοχής λόγω παραμονής του υλικού σε περιβάλλον υψηλής θερμοκρασίας. Η υποβάθμιση αυτή
προσδιορίστηκε ποσοτικά σαν συνάρτηση της θερμοκρασίας και του χρόνου έκθεσης. Η μεθοδολογία σχεδιασμού στηρίζεται σε μεγάλο βαθμό στην ανάλυση και προσομοίωση της
λειτουργίας στοιχείων κατασκευών με την μέθοδο των Πεπερασμένων Στοιχείων. Σημαντικό μέρος της
παρούσας εργασίας αφορά την ανάπτυξη υπολογιστικού κώδικα ο οποίος επιτυγχάνει την προσαρμογή
του πρωτότυπου μοντέλου υλικού σε εμπορικό λογισμικό ανάλυσης με ΠΣ. Επιπρόσθετα ο
υπολογιστικός κώδικας εφαρμόζει μοντελοποίηση προοδευτικής αστοχίας που περιλαμβάνει τρείς
ξεχωριστούς μηχανισμούς δομικής αστοχίας. Τέλος, ο κώδικας αυτός χρησιμοποιείται στην
προσομοίωση της λειτουργίας ενός τυπικού θαλάμου καύσης στροβιλομηχανής παραγωγής ενέργειας σε
συνθήκες σταθερής κατάστασης (steady state), κατασκευασμένου από στρωματοποιημένο ΣΚΥ
συνεχών ινών και παρουσιάζονται τα αποτελέσματα της ανάλυσης. / -
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