Final Theses

One of the main components of hydropower plants is the electrical generator converting mechanical to electrical energy. Despite the very high efficiency, dissipation occurs due to electromagnetic losses and must be removed from the system. For this purpose, a thermodynamic cycle is realized providing the required cooling air to the critical devices. A model of a hydro generator is currently in the design process, that will enable a detailed experimental analysis of the cooling flow.

The reduction of climate-damaging greenhouse gases requires modern combustion concepts based on hydrogen combustion. The combustion of hydrogen implies novel turbine inlet conditions. The approval of novel engines with hydrogen combustion requires comprehensive experimental investigations of the impact of hydrogen combustion on the high-pressure turbine. For this reason, a variable turbulence generator for investigations within the Large Scale Turbine Rig will be designed at the GLR in cooperation with Rolls-Royce Deutschland. As a first step of the research project a turbulence generator that meets the required turbine inlet conditions has to be designed numerical. Within this MTh, a numerical setup has to be created, a parameter study to identify sensitivities on the turbine inlet conditions has to be conducted and a geometry for the turbulence generator has to be derived that fulfils all aerodynamic requirements.

Aerothermal optimization is state-of-the-art in the development of modern gas turbines and jet engines. Current research at the Large Scale Turbine Rig (LSTR) focuses on outer endwall cooling geometries and their effect on the outer annulus flow. PSP is an optical measurement technique that allows the determination of the film cooling effectiveness and comes along with a high spatial resolution. Within this thesis a new approach has to be developed for thermal measurements at the outer endwall. Therefore, a application of the existing PSP setup on the new experimental task as well as pre-tests have to be conducted. Goal of the thesis is a feasible setup for PSP measurements at the outer endwall of the LSTR and the conduction of PSP measurements.

The challenging requirements of modern jet engines and gas turbines have led to complex, highly 3-d flow mechanisms that are even coupled with other disciplines (structure, thermal management). To gain an understanding and further improve modern jet engines and gas turbines, experimental investigations are mandatory. To account for the complex, highly 3-d flow mechanisms experimental investigations in the turbomachinery laboratory are continuously transforming to high-sophisticated measurement techniques. Therefore, the test facility of the GLR needs a wind tunnel that allows the testing and development of new, capable and highly- accurate measurement techniques. The concept development of a measurement testing wind tunnel within this ADP is the first step for the development of highly-sophisticated measurement techniques. Scope of this ADP is the design of the flow path, the probe traversing system, the experimental accessibility as well as the control mechanisms for operating point and data acquisition.

The reduction of climate-damaging greenhouse gases requires modern combustion concepts based on hydrogen combustion. The combustion of hydrogen implies novel turbine inlet conditions. The approval of novel engines with hydrogen combustion requires comprehensive experimental investigations of the impact of hydrogen combustion on the high-pressure turbine. For this reason, a variable turbulence generator for investigations within the Large Scale Turbine Rig will be designed at the GLR in cooperation with Rolls-Royce Deutschland. As a first step of the research project a turbulence generator that meets the required turbine inlet conditions has to be designed numerical. Within this MTh, a numerical setup has to be created, a parameter study to identify sensitivities on the turbine inlet conditions has to be conducted and a geometry for the turbulence generator has to be derived that fulfils all aerodynamic requirements.