Highly Accurate Delta Efficiency Measurements at the Large Scale Turbine Rig

Eitenmüller, Johannes; Wilhelm, Manuel; Gresser, Leonhard; Ostrowksi, Tom; Leichtfuß, Sebastian; Schiffer, Heinz-Peter; Lyko, Christoph; Naik, S.

doi:10.1115/gt2019-90294

Cited by 6 publications

(4 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…To quantify an absolute measurement uncertainty for a compressor rig is challenging (e.g. Eitenmüller et al, 2019). It has to be differentiated between uncertainties due to the measurement systems (e.g.…”

Section: Measurement Uncertaintymentioning

confidence: 99%

Transonic compressor Darmstadt - Open test case Introduction of the TUDa open test case

Klausmann

Franke

Foret

et al. 2022

J. Glob. Power Propuls. Soc.

View full text Add to dashboard Cite

Designs for future aero engines aim for increased efficiency with reduced exhaust gas and noise emissions. To achieve these goals, comprehensive physical understanding and highly innovative solutions are necessary. Even though computational capabilities are rising, the required confidence level is restrained. To understand and validate theoretical and numerical models, extensive experiments at realistic operating conditions are crucial. The modular compressor at the Transonic Compressor Darmstadt test facility at Technical University of Darmstadt enables investigations of prototype BLISK rotors in single or 1.5-stage setups, operating at high-speed conditions. Extensive steady and time-resolving instrumentation is used to determine the compressor aerodynamics and performance as well as aeroelastics. To foster improvements in numerical modelling and predictability based on high quality experimental data, the TUDa-GLR-OpenStage test case is introduced. It comprises a single stage setup, including the BLISK rotor, a 3D-optimized stator as well as the annulus contour. The data set is supplemented with comprehensive measurement data at stage inlet and outlet as well as running tip clearances. This paper describes the open test case, related geometries, measurement procedures and corresponding experimental results, including steady state performance and unsteady aerodynamics. Ultimately, it is aiming to provide a standard case for future development of numerical models and comparable validation.

show abstract

Section: Measurement Uncertaintymentioning

confidence: 99%

Transonic compressor Darmstadt - Open test case Introduction of the TUDa open test case

Klausmann

Franke

Foret

et al. 2022

J. Glob. Power Propuls. Soc.

View full text Add to dashboard Cite

show abstract

“…All operating parameters are specific for the tested turbine and lead to an engine-realistic Reynolds number and a turbine specific flow coefficient at the rotor inlet. Further information on the operating parameters, their uncertainties, rig stability and repeatability are summarized in Eitenmüller et al [22].…”

Section: Experimental Approachmentioning

confidence: 99%

High-resolution heat transfer measurements on a rotating turbine endwall with infrared thermography

Ostrowski

Schiffer

2021

Meas. Sci. Technol.

View full text Add to dashboard Cite

Computational thermo-fluid dynamics in the field of turbo machinery research tend to account for transient interaction mechanisms to predict the convective heat transfer within the hot gas path. In this context, the rotor hub side endwall region of the high pressure turbine depicts an object of interest as the near wall flow field may be dominated by rotating flow structures emerging from the disc space cavities. The validation of the applied numerical tools rely on experimental heat transfer setups reproducing such transient boundary conditions. This paper describes an experimental approach to quantify the heat transfer coefficient and the adiabatic wall temperature on the rotating endwall of a large scale test turbine. The wall heat flux distribution in a thin film isolator coated to a well conducting support structure is quantified for a series of quasi-isothermal boundary conditions. A high-resolution infrared camera is used to capture triggered thermograms of the rotating surface. Distributed thermocouples in the base body serve as reference points for camera calibration and to deduce the temperature distribution at the interface to the isolator. The calibration is in-situ and includes the pixel-wise quantification of uncertainties in the surface temperatures. An advanced linear fit approach is applied to derive the unknown adiabatic quantities and their uncertainties. For the examined operating point with a rim seal purge flow rate of 1% the random part of the relative measurement uncertainty is clearly below 10% for the heat transfer coefficient and below 5% for the adiabatic wall temperature. As the evaluation algorithm is designed to consider covariances between the thermocouple and infrared readings, the surface wall heat flux can be evaluated for every single infrared image.

show abstract

“…The operating point of the rig is summarized in Figure 1. Further details on rig control and stability are provided by Eitenmüller et al [7].…”

Section: The Large Scale Turbine Rigmentioning

confidence: 99%

Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint

Wilhelm

Schiffer

2019

IJTPP

Self Cite

View full text Add to dashboard Cite

Rotor tip film cooling is investigated at the Large Scale Turbine Rig, which is a 1.5-stage axial turbine rig operating at low speeds. Using pressure sensitive paint, the film cooling effectiveness η at a squealer-type blade tip with cylindrical pressure-side film cooling holes is obtained. The effect of turbine inlet swirl on η is examined in comparison to an axial inflow baseline case. Coolant-to-mainstream injection ratios are varied between 0.45% and 1.74% for an engine-realistic coolant-to-mainstream density ratio of 1.5. It is shown that inlet swirl causes a reduction in η for low injection ratios by up to 26%, with the trailing edge being especially susceptible to swirl. For injection ratios greater than 0.93%, however, η is increased by up to 11% for swirling inflow, while for axial inflow a further increase in coolant injection does not transfer into a gain in η .

show abstract

Highly Accurate Delta Efficiency Measurements at the Large Scale Turbine Rig

Cited by 6 publications

References 0 publications

Transonic compressor Darmstadt - Open test case Introduction of the TUDa open test case

Transonic compressor Darmstadt - Open test case Introduction of the TUDa open test case

High-resolution heat transfer measurements on a rotating turbine endwall with infrared thermography

Experimental Investigation of Rotor Tip Film Cooling at an Axial Turbine with Swirling Inflow Using Pressure Sensitive Paint

Contact Info

Product

Resources

About