Large Scale Turbine Rig (LSTR)

The LSTR is a low Mach turbine test rig, carrying a scaled 1.5-stage axial high-pressure turbine geometry. The rig is operated in a closed-loop setup and allows to control the main flow temperature. To simulate engine-representative inflow conditions, the LSTR is equipped with a combustor module and exchangable swirlers. Further inflow conditions include axial or turbulent inflow as well as altered relative positions of swirler cores and NGVs by traversing casing rings.

In addition to the investigation of turbine aerodynamics, the rig is set up for detailed research in the field of turbine cooling technology. The facility is equipped with an extensive secondary air system. Up to eight cooling streams can be individually controlled in respect to mass flow.

Moreover, the LSTR offers a large number of optical and physical access ports as well as high flexibility to the application of measurement techniques. The rig is operated to meet engine realistic Reynolds numbers allowing the transfer of results to real gas turbines.

Nominal Power primary air system (max.): 931 kW
Nominal Power secondary air system (max.): 400 kW
Maximum mass flow: 15k g/s
Pressure ratio: up to 1.55
Turbine revolutions: up to 1000 rpm
Hub diameter: 868 mm

AG TURBO COOREFlex-Turbo 3.1.2 – Aerothermal combuster-turbine interaction: Rotor hub side endwall

Objective of this project is the experimental investigation of the heat transfer on high pressure turbine rotor hub side endwalls. Flow mechanics and thermodynamics in that region are highly complex. Complying the requirements with respect to structural and thermal loads are crucial for the safe and durable operation of gas turbines. To fulfill the requirements extensive cooling technologies are applied. For the rotor hub side endwall this also means to avoid hot gas ingress into the cavity between stator and rotor. As all cooling flows, this sealing air is extracted from the compressor and bypasses the combustor. The so called rim seal purge flow than interacts with the main flow. Both phenomena have a negative effect on turbine efficiency.

Industry partner is Alstom Power. The project is partly funded by the Federal Republic of Germany, Minstry for Economic Affairs and Energy, within the framework of AG Turbo.

AG TURBO COOREFlex-Turbo 3.1.1 – Combuster turbine interaction: cooling efficiency and aerodynamics in the rotor tip region

This project is focusing on the effect of modern combustor technologies on aerodynamics and cooling effectiveness in the rotor tip region of the first high pressure turbine. Goal is the optimization of the combustor-turbine interface as well as a more effective use of cooling air in the tip region leading towards greater turbine efficiency.

Industry partners are Rolls-Royce Deutschland and Alstom Power. The project is partly funded by the Federal Republic of Germany, Minstry for Economic Affairs and Energy, within the framework of AG Turbo.

AG TURBO 2020 3.2.5 – Aerothermal Combustor Turbine Interaction

The content of this research project is the investigation of heat transfer and film cooling effectiveness on the hub side endwall of the nozzle guide vane, the first stator stage in the high pressure turbine. The impact of swirling combustor inflow and varied coolant injection rates is studied on a high pressure turbine blading, scaled to low Mach number conditions. In addition, film cooling effectiveness is studied on the NGV airfoil. The thermal measurement techniques infrared thermography and tracer gas measurements are used to gain the experimental data. For the project, a new turbine casing was designed, offering extensive optical and physical access to the measurement section.

Goal of the project is to achieve a better understanding of the impact of lean combustors on the design of future high pressure turbines.

Industry partners are Rolls-Royce Deutschland and Alstom Power. The project is partly funded by the Federal Republic of Germany, Minstry for Economic Affairs and Energy, within the framework of AG Turbo.

AG TURBO 2020 3.2.1A – Aerodynamic combustor turbine interaction

The project aims to investigate the effects of swirl flow typical for modern lean burn combustors on the aerodynamics of the first high pressure turbine stage. The focus is the detailed investigation of hub side endwall cooling aerodynamics in front of the first nozzle guide vane.

Within the scope of this project the measurement section is modified to allow the generation of a turbine inlet flow field which is typical for lean burn combustors. Furthermore this combustor module is equipped with varies physical and optical access to allow detailed aerodynamic measurements. The hub side endwall cooling is also realized modularly to allow geometry variation.

Industry partners is Rolls-Royce Deutschland and Alstom Power. The project is partly funded by the Federal Republic of Germany, Minstry for Economic Affairs and Energy, within the framework of AG Turbo.