The Engine 3E Core Engine

Klinger, Holger; Lazik, Waldemar; Wunderlich, Thomas

doi:10.1115/gt2008-50679

Cited by 21 publications

(11 citation statements)

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“…The LSTR swirler was modeled based on the Engine-3-E-swirler (Klinger et al [23]) and consists of three concentric rings with curved blades (Figure 1). Two inner rings with high airflow turning angles of 50 • created a strong swirl in the counter-clockwise direction with respect to the main flow direction.…”

Section: Large Scale Turbine Rig Swirlermentioning

confidence: 99%

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Werschnik

Schneider

Herrmann

et al. 2017

IJTPP

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The aerothermal interaction of the combustor exit flow on the first vane row has been examined at the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt (Darmstadt, Germany). A baseline configuration of axial inflow and a variation of swirling combustor inflow have been studied. The nozzle guide vane (NGV) featured endwall cooling, airfoil film cooling and a trailing edge slot ejection as well as NGV-rotor wheel space purge flow. CO 2 is injected for coolant flow tracing. The results are compared to five hole probe (5HP) measurements. The experiments for the baseline configuration are accompanied by numerical simulations using a passive scalar tracking method to validate the results and study the propagation of the coolant flow. The endwall coolant injection is detected to influence the pressure losses in the NGV. It has an impact on the Trailing Edge (TE) coolant ejection as well. For swirling combustor inflow, increased NGV pressure losses and increased mixing of Rear Inner Discharge Nozzle (RIDN) coolant and main flow is observed. An influence of the clocking position of the swirler to the vane is detected. Additional losses within the NGV row can be assigned to the swirler by means of flow tracing.

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Section: Large Scale Turbine Rig Swirlermentioning

confidence: 99%

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Werschnik

Schneider

Herrmann

et al. 2017

IJTPP

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“…Using the example of an E3E [11] high pressure compressor's first stage ( Fig. 1), the results of experimental mistuning identification based on blade by blade measurements [10,12], model updating [12] and the simulation of the aeroelastic behavior are presented.…”

Section: Introductionmentioning

confidence: 99%

Modal and Aeroelastic Analysis of a Compressor Blisk Considering Mistuning

Nipkau

Kühhorn

Beirow

2011

Volume 6: Structures and Dynamics, Parts a and B

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Focussing on three basic blade modes the effect of the flow's influence on the forced response of a mistuned HPCblisk is studied using a surrogate lumped mass model called equivalent blisk model (EBM). Both measured and intentionally allowed mistuning is considered to find out in principle if the flow contributes to a slowdown of blade displacements with increasing mistuning. In a first step the mechanical properties of the EBM are adjusted to a finite element model and known mistuning distributions given in terms of blade frequencies and damping. Taking into account the flow structure interaction CFD-computations are carried out in order to derive aerodynamic influence coefficients (AIC) which are used to describe the aerodynamic forces coming along with the motion of each blade in the flow. These aerodynamic forces can be included directly in the EBM equations of motion or alternatively be used to calculate aeroelastic eigenvalues from which additional equivalent aerodynamic elements representing the co-vibrating air mass as well as aerodynamic stiffening and damping effects are derived. Both kinds of EBM are applied to study the forced response at least in a qualitative manner aiming to demonstrate some basic effects at low computing time. NOMENCLATURE1F first blade flap mode 1T first blade torsion mode 1TL first blade tramline mode AIC aerodynamic influence coefficients CFD computational fluid dynamics DFT discrete fourier transform DOF degree of freedom E3E Engine 3E (technology program)

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“…A modern industrial high pressure compressor, depicted in Figure 1 is here used for the simulations (Klinger et al, 2008(Klinger et al, , 2011. Practical 3D geometries and operation points have been provided by an industrial partner.…”

Section: Case Descriptionmentioning

confidence: 99%

Aeroelastic assessment of a highly loaded high pressure compressor exposed to pressure gain combustion disturbances

Almeida

Peitsch

2018

J. Glob. Power Propuls. Soc.

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A numerical aeroelastic assessment of a highly loaded high pressure compressor exposed to flow disturbances is presented in this paper. The disturbances originate from novel, inherently unsteady, pressure gain combustion processes, such as pulse detonation, shockless explosion, wave rotor or piston topping composite cycles. All these arrangements promise to reduce substantially the specific fuel consumption of present-day aeronautical engines and stationary gas turbines. However, their unsteady behavior must be further investigated to ensure the thermodynamic efficiency gain is not hindered by stage performance losses. Furthermore, blade excessive vibration (leading to high cycle fatigue) must be avoided, especially under the additional excitations frequencies from waves traveling upstream of the combustor. Two main numerical analyses are presented, contrasting undisturbed with disturbed operation of a typical industrial core compressor. The first part of the paper evaluates performance parameters for a representative blisk stage with high-accuracy 3D unsteady Reynolds-averaged Navier-Stokes computations. Isentropic efficiency as well as pressure and temperature unsteady damping are determined for a broad range of disturbances. The nonlinear harmonic balance method is used to determine the aerodynamic damping. The second part provides the aeroelastic harmonic forced response of the rotor blades, with aerodynamic damping and forcing obtained from the unsteady calculations in the first part. The influence of blade mode shapes, nodal diameters and forcing frequency matching is also examined.

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The Engine 3E Core Engine

Cited by 21 publications

References 0 publications

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Modal and Aeroelastic Analysis of a Compressor Blisk Considering Mistuning

Aeroelastic assessment of a highly loaded high pressure compressor exposed to pressure gain combustion disturbances

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