Critical myths in drama as education

Drama as education is a relatively young concern, which has been primarily occupied with developing a strong tradition of practice. As a result it has suffered from a dearth of theoretical and critical engagement. This situation has led to the existence of a range of unquestioned beliefs and practices that underpin much of the governance, traditions, knowledge and operation of drama in educational settings. The thesis examines the existence and location of the community of drama as education, reviews the discourse of the community, and seeks to understand previous attempts at demythologising. This thesis proposes a critical understanding of the idea of myth in order that it can be used in a positive and beneficial manner. Utilising a post-modern critical research methodology, it constructs a bricolage of theoretical perspectives that collectively are used to locate, identify and interrogate areas of myth. A new typography of myth reveals four dominant areas of operation, and examines the manner in which myths impact upon the educational and cultural institutions in which they occur. The forces that conceive of, operate and perpetuate myth are understood to be language, power and ideology. These elements operate in conjunction with each other, with human agency at the helm. The thesis is in nine chapters. Chapter 1 sets the scene and introduces the range of the research. It is followed by Chapter 2 which seeks to put in place a range of theoretical perspectives upon which the methodology is constructed. Chapter 3 provides further theoretical insight into the location of the research, and Chapter 4 constructs a critical mythic bricolage, defines its usage, and proposes a contemporary typology of myth. Chapter 5 identifies the ‘Point of Entry Text’ – the primary school drama curriculum in the Republic of Ireland, and deals with the category of governing myths. Chapter 6 is concerned with traditional myths, Chapter 7 examines epistemological myths, and Chapter 8 teases out operational myths. Finally, Chapter 9 looks to the future of myth after demythologising, and seeks to begin engaging with the inevitable process of remythologising.EThOS - Electronic Theses Online ServiceGBUnited Kingdo

Multidisciplinary assessment of a year 2035 turbofan propulsion system

A conceptual design of a year 2035 turbofan is developed and integrated onto a year 2035 aircraft model. The mission performance is evaluated for CO2, noise and NOx and is compared with a notional XWB/A350-model. An OGV heat exchanger is then studied rejecting heat from an electric generator, and its top-level performance is evaluated. The fan, the booster and the low-pressure turbine of the propulsion system are subject to more detailed aero design based on using commercial design tools and CFD-optimization. Booster aerodynamic modelling output is introduced back into the performance model to study the integrated performance of the component. The top-level performance aircraft improvements are compared to top-level-trends and ICAO estimates of technology progress potential, attempting to evaluate whether there is some additional margin for efficiency improvement beyond the ICAO technology predictions for the same time frame

Sensitivity of Aeroelastic Properties of an Oscillating LPT Cascade

Modern turbomachinery design is characterized by a tendency towards thinner, lighter and highly loaded blades, which in turn gives rise to increased sensitivity to flow induced vibration such as flutter. Flutter is a self-excited and self-sustained instability phenomenon that may lead to structural failure due to High Cycle Fatigue (HCF) or material overload. In order to be able to predict potential flutter situations, it is necessary to accurately assess the unsteady aerodynamics during flutter and to understand the physics behind its driving mechanisms. Current numerical tools used for predicting unsteady aerodynamics of vibrating turbomachinery components are capable of modeling the flow field at high level of detail, but may fail in predicting the correct unsteady aerodynamics under certain conditions. Continuous validation of numerical models against experimental data therefore plays significant role in improving the prediction accuracy and reliability of the models.   In flutter investigations, it is common to consider aerodynamically symmetric (tuned) setups. Due to manufacturing tolerances, assembly inaccuracies as well as in-service wear, the aerodynamic properties in a blade row may become asymmetric. Such asymmetries can be observed both in terms of steady as well as unsteady aerodynamic properties, and it is of great interest to understand the effects this may have on the aeroelastic stability of the system.   Under certain conditions vibratory modes of realistic blade profiles tend to be coupled i.e. the contents of a given mode of vibration include displacements perpendicular and parallel to the chord as well as torsion of the profile. Current design trends for compressor blades that are resulting in low aspect ratio blades potentially reduce the frequency spacing between certain modes (i.e. 2F & 1T). Combined modes are also likely to occur in case of the vibration of a bladed disk with a comparatively soft disk and rigid blades or due to tying blades together in sectors (e.g. in turbines).   The present investigation focuses on two areas that are of importance for improving the understanding of aeroelastic behavior of oscillating blade rows. Firstly, aeroelastic properties of combined mode shapes in an oscillating Low Pressure Turbine (LPT) cascade were studied and validity of the mode superposition principle was assessed. Secondly, the effects of aerodynamic mistuning on the aeroelastic properties of the cascade were addressed. The aerodynamic mistuning considered here is caused by blade-to-blade stagger angle variations   The work has been carried out as compound experimental and numerical investigation, where numerical results are validated against test data. On the experimental side a test facility comprising an annular sector of seven free-standing LPT blades is used. The aeroelastic response phenomena were studied in the influence coefficient domain where one of the blades is made to oscillate in three-dimensional pure or combined modes, while the unsteady blade surface pressure is acquired on the oscillating blade itself and on the non-oscillating neighbor blades. On the numerical side, a series of numerical simulations were carried out using a commercial CFD code on a full-scale time-marching 3D viscous model. In accordance with the experimental part the simulations are performed using the influence coefficient approach, with only one blade oscillating.   The results of combined modes studies suggest the validity of combining the aeroelastic properties of two modes over the investigated range of operating parameters. Quality parameters, indicating differences in mean absolute and imaginary values of the unsteady response between combined mode data and superposed data, feature values that are well below measurement accuracy of the setup.   The findings of aerodynamic mistuning investigations indicate that the effect of de-staggering a single blade on steady aerodynamics in the cascade seem to be predominantly an effect of the change in passage throat. The changes in steady aerodynamics are thereby observed on the unsteady aerodynamics where distinctive effects on flow velocity lead to changes in the local unsteady pressure coefficients. In order to assess the overall aeroelastic stability of a randomly mistuned blade row, a Reduced Order Model (ROM) model is introduced, allowing for probabilistic analyses. From the analyses, an effect of destabilization due to aero-asymmetries was observed. However the observed effect was of moderate magnitude.QC 20130610Turbokraf

UTILIZATION OF WIND POWER IN RWANDA: Design and Production Option

This Master Thesis is the research done in the country of Rwanda. The project leads to study the climate of this country in order to establish whether this climate could be used to produce energy from air and to implement the first wind turbine for serving the nation.   After an introduction about the historical background of wind power, the thesis work deals with assessment of wind energy potential of Rwanda in focusing of the most suitable place for wind power plants. The best location with annual mean wind speed, the rate of use of turbine with hub height for an annual production per year, the mean wind speeds for 6 sites of Rwanda based on ECMWF for climatic data for one year at relief of altitude of 100m and coordinates are reported too.   The result of energy produced and calculations were done based on power hitting wind turbine generator in order to calculate Kinetic energy and power available at the best location to the measurement over the period of 12 months, that could be hoped for long term.   With help of logarithmic law, where wind speed usually increases with increasing in elevation and the desired wind speeds at all 6 sites were used. The annual energy production was taken into account at the best site with desired wind speed at the initial cost of turbine as well as the cost of energy (COE).However, with comparison of the tariff of EWSA, the price of Wind designed in this Research per kWh is cheaper and suitable for people of Rwanda.I WISH TO PUBLISH MY THESIS</p

Steady-state aerodynamics tip gap influence in atransonic linear cascade at near stall

A comparison of steady-state aerodynamics for two tip gap configurations in the KTH transonic linear cascade is presented. The experimental campaign is performed for 1% and 2% tip clearances. The operational point is representative of an open-source virtual compressor (VINK) operating near stall at part speed. The inlet Mach number (Mach 0:81) is above its airfoil critical value with a high incidence angle, producing a leading edge separation bubble. The measurement plane is at 85% span for each tip gap configuration. Steady-state aerodynamic measurements are presented at the passage and downstream the blades. The blade loading at the passages of interest is mapped by a set of instrumented blades containing 15 pressure taps. The downstream conditions are reconstructed by five-hole probe measurements. Numerical results are computed by the commercial software ANSYS CFX. A comparison of experimental and numerical data is presented to identify correlations and limitations. The scope of this paper is to experimentally and numerically determine the influence of tip gap variation in the steady-state aerodynamics in a transonic linear cascade where leading edge separation occurs.QC 20230620</p

UTILIZATION OF WIND POWER IN RWANDA: Design and Production Option

This Master Thesis is the research done in the country of Rwanda. The project leads to study the climate of this country in order to establish whether this climate could be used to produce energy from air and to implement the first wind turbine for serving the nation.   After an introduction about the historical background of wind power, the thesis work deals with assessment of wind energy potential of Rwanda in focusing of the most suitable place for wind power plants. The best location with annual mean wind speed, the rate of use of turbine with hub height for an annual production per year, the mean wind speeds for 6 sites of Rwanda based on ECMWF for climatic data for one year at relief of altitude of 100m and coordinates are reported too.   The result of energy produced and calculations were done based on power hitting wind turbine generator in order to calculate Kinetic energy and power available at the best location to the measurement over the period of 12 months, that could be hoped for long term.   With help of logarithmic law, where wind speed usually increases with increasing in elevation and the desired wind speeds at all 6 sites were used. The annual energy production was taken into account at the best site with desired wind speed at the initial cost of turbine as well as the cost of energy (COE).However, with comparison of the tariff of EWSA, the price of Wind designed in this Research per kWh is cheaper and suitable for people of Rwanda.I WISH TO PUBLISH MY THESIS</p

Steady-state aerodynamics tip gap influence in atransonic linear cascade at near stall

A comparison of steady-state aerodynamics for two tip gap configurations in the KTH transonic linear cascade is presented. The experimental campaign is performed for 1% and 2% tip clearances. The operational point is representative of an open-source virtual compressor (VINK) operating near stall at part speed. The inlet Mach number (Mach 0:81) is above its airfoil critical value with a high incidence angle, producing a leading edge separation bubble. The measurement plane is at 85% span for each tip gap configuration. Steady-state aerodynamic measurements are presented at the passage and downstream the blades. The blade loading at the passages of interest is mapped by a set of instrumented blades containing 15 pressure taps. The downstream conditions are reconstructed by five-hole probe measurements. Numerical results are computed by the commercial software ANSYS CFX. A comparison of experimental and numerical data is presented to identify correlations and limitations. The scope of this paper is to experimentally and numerically determine the influence of tip gap variation in the steady-state aerodynamics in a transonic linear cascade where leading edge separation occurs.QC 20230620</p

Blade oscillation mechanism for aerodynamic damping measurements at high reduced frequencies

Accurate prediction of aerodynamic damping is essential for flutter and forced response analysis of turbomachinery components. Reaching a high level of confidence in numerical simulations requires that the models have been validated against the experiments. Even though a number of test cases have been established over the past decades, there is still a lack of suitable detailed test data that can be used for validation purposes in particular when it comes to aero damping at high reduced frequencies which is more relevant in the context of forced response analysis. A new transonic cascade test rig, currently undergoing commissioning at KTH, has been designed with the goal to provide detailed blade surface unsteady pressure data for compressor blades profiles oscillating at high reduced frequencies. The paper provides an overview of the blade actuation system employed in the test rig and presents the result of a series of bench tests characterizing the blade vibration amplitudes achieved with this actuation system

Validation of unsteady aerodynamics in a transonic linear cascade at first flex modeshape at near stall conditions

Experimental and numerical, are presented in the transonic linear cascade (TLC) at KTH. Numerical results are recovered by SST turbulence model with a reattachment modification (RM) from commercial software Ansys CFX. This paper aims to compare the current numerical methods as a step towards producing open data for validation purposes. The operational point is representative of an open source virtual compressor (VINK) operating near stall at part speed, with an induced leading edge separation bubble at an inlet Mach number of 0.81. Steady-state results consists of Laser-2-Focus anemometer (L2F), blade loading, flow visualization and five-hole probe measurements. Steady-state numerical results indicate an over prediction of low momentum regions in the passages and under prediction of a separation bubble. The cascade operates in the influence coefficient domain, where the central blade vibrates in its first natural mode shape with 0.69 reduced frequency. Unsteady pressure coefficients display an amplitude discrepancy between methods. Numerically, the unsteady pressure content at the measurement plane (85% span) is dominated by the oscillation of the tip leakage vortex, which is not observed from experimental data. Despite a qualitative mismatch with the unsteady  pressure amplitude, the phase- lag shows good agreement between both methods, which is of high relevance when predicting the aerodynamic damping.QC 20230619ADiS

Validation of unsteady aerodynamics in a transonic linear cascade at first flex modeshape at near stall conditions

Experimental and numerical, are presented in the transonic linear cascade (TLC) at KTH. Numerical results are recovered by SST turbulence model with a reattachment modification (RM) from commercial software Ansys CFX. This paper aims to compare the current numerical methods as a step towards producing open data for validation purposes. The operational point is representative of an open source virtual compressor (VINK) operating near stall at part speed, with an induced leading edge separation bubble at an inlet Mach number of 0.81. Steady-state results consists of Laser-2-Focus anemometer (L2F), blade loading, flow visualization and five-hole probe measurements. Steady-state numerical results indicate an over prediction of low momentum regions in the passages and under prediction of a separation bubble. The cascade operates in the influence coefficient domain, where the central blade vibrates in its first natural mode shape with 0.69 reduced frequency. Unsteady pressure coefficients display an amplitude discrepancy between methods. Numerically, the unsteady pressure content at the measurement plane (85% span) is dominated by the oscillation of the tip leakage vortex, which is not observed from experimental data. Despite a qualitative mismatch with the unsteady  pressure amplitude, the phase- lag shows good agreement between both methods, which is of high relevance when predicting the aerodynamic damping.QC 20230619ADiS