Influence of the Incorrect Settings of Axial Compressor Inlet Variable Stator Vanes on Gas Turbine Engine Work Parameters

Wirkowski, P.

doi:10.5604/12314005.1138659

Cited by 6 publications

(5 citation statements)

References 2 publications

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“…Previous experimental and numerical investigations [13,14] have focused on understanding the aerodynamic phenomena related to blade articulation within the compressor section of the gas turbine engine. Due to the lack of mechanism for rotor blade articulation, these studies provided limited information on rotor blade articulation.…”

Section: Introductionmentioning

confidence: 99%

High-Fidelity Finite Element Modeling and Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interaction at Off-Design Conditions

Kozak

Rajanna

et al. 2020

J. mech.

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The objective of this work is to computationally investigate the impact of an incidence-tolerant rotor blade concept on gas turbine engine performance under off-design conditions. When a gas turbine operates at an off-design condition such as hover flight or takeoff, large-scale flow separation can occur around turbine blades, which causes performance degradation, excessive noise, and critical loss of operability. To alleviate this shortcoming, a novel concept which articulates the rotating turbine blades simultaneous with the stator vanes is explored. We use a finite-element-based moving-domain computational fluid dynamics (CFD) framework to model a single high-pressure turbine stage. The rotor speeds investigated range from 100% down to 50% of the designed condition of 44,700 rpm. This study explores the limits of rotor blade articulation angles and determines the maximal performance benefits in terms of turbine output power and adiabatic efficiency. The results show articulating rotor blades can achieve an efficiency gain of 10% at off-design conditions thereby providing critical leap-ahead design capabilities for the U.S. Army Future Vertical Lift (FVL) program.

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Section: Introductionmentioning

confidence: 99%

High-Fidelity Finite Element Modeling and Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interaction at Off-Design Conditions

Kozak

Rajanna

et al. 2020

J. mech.

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“…The rotation angle of the vane in a complete cycle is calculated according to Eq. (18), and the rotation speed is obtained by differentiating the time with the rotation angle. The results are shown in Figure 11, it can be seen that the rotation range of the vane is 60° to 120°.…”

Section: Tribo-dynamics Analysis Of the Vsv Mechanism 51 Rotation Anmentioning

confidence: 99%

“…The VSV mechanism of compressor is the most important motion adjusting mechanism in the engine, which can prevent the compressor from surging and effectively improve the overall efficiency of the engine by changing the vane angle to adjust the incoming angle of attack, and is widely used in modern aeroengines [18][19][20].…”

Section: Introductionmentioning

confidence: 99%

A rough surface damping contact model and its application in spatial variable stator vane mechanism with dry friction joint

Cheng

Meng

et al. 2021

Preprint

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For the mechanical system without oil lubrication, the impact or collision often occurs in the joint clearance, such as the variable stator vane (VSV) mechanism. In the dry friction joint, the damping of the contact bodies has a significant effect on the simulation stability of the tribo-dynamics calculation process. In order to investigate the effect of contact damping and joint clearance on the VSV mechanism performance, this paper proposes a damping contact model on rough surfaces to calculate the clearance contact force between the trunnion and bushing, and the spatial tribo-dynamics of VSV is established by combining this model with spatial dynamics. In addition, the effect of clearance size on the tribo-dynamics is analyzed. The results show that the contact damping must be included in the contact force model of dry friction joints, otherwise the calculation process will oscillate or even not converge, but the contact damping effect can be ignored in the case of lubricating oil. The movement of the trunnion in the bushing is affected by the adjustment drive and the aerodynamic drag, which leads to the wear concentrated on the edge of the bushing. The clearance size affects the distribution of the damping forces and the rigid forces in the contact process, and the damping forces ensure the stability of the VSV tribo-dynamics simulation process. Moreover, with the increase of clearance, the adjustment accuracy of the VSV mechanism is reduced, and the wear of the bushing is intensified.

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“…Wang et al [20] conducted computational analysis to demonstrate the performance benefits possible by articulating stator blades on a marine gas turbine engine and reported improvements in efficiency and fuel consumption. Wirkowski [21] completed an experimental study on a marine gas turbine engine with variable compressor stator blades also reporting improved engine performance. Similarly, Cyrus [22] measured several flow parameters to create a detailed flow field and obtained performance data of the unsteady flow within an axial compressor stage featuring stator and rotor articulation.…”

Section: Fig 1 Schematic Of Proposed Concept For Turbomachinery Bladmentioning

confidence: 99%

Computational Finite Element Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interactions for Future Vertical Lift Propulsion

Kozak

Bravo

Murugan

et al. 2019

AIAA Propulsion and Energy 2019 Forum

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The objective of this work is to computationally investigate the impact of an incident-tolerant rotor blade concept on gas-turbine engine performance under off-design conditions. Currently, gas-turbine engines are designed to operate at a single condition with nearly fixed rotor speeds. Operation at off-design conditions, such as during hover flight or during takeoff, causes the turbine blade flow to excessively separate introducing performance degradations, excessive noise, and critical loss of operability. To address these issues, the benefits of using an incidence-tolerant rotor blade concept is explored based on a novel concept that articulates the rotating turbine blade synchronously with the stator nozzle vanes. This concept is investigated using a novel CFD/FSI framework based on finite element analysis. The model considers a complex single stage highpressure turbine geometry with 24 stator and 34 rotor blades operating under combustor exit flow conditions. The rotor speeds investigated are 44,700 rpm, 33,525 rpm, and 22,350 rpm corresponding to the design point at 100% speed down to 51% speed during off-design flight mode. This study focuses on determining the optimal performance benefits possible by exploring the limits of rotor blade articulation angles, as well as reporting its impact over a broad range of rotor speeds at Army relevant conditions. The key variables of interest include moments on the blade suction surface, torque, power, and turbine stage adiabatic efficiency. Further, sensitivity analysis of the uncertainties in boundary conditions is conducted to determine its influence on turbine efficiency. The results show that it is possible to increase efficiency increases of up to 10% by articulating rotor blades at off-design conditions thereby providing critical leap ahead design capabilities for the US Army Future Vertical Lift (FVL) program.

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Influence of the Incorrect Settings of Axial Compressor Inlet Variable Stator Vanes on Gas Turbine Engine Work Parameters

Cited by 6 publications

References 2 publications

High-Fidelity Finite Element Modeling and Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interaction at Off-Design Conditions

High-Fidelity Finite Element Modeling and Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interaction at Off-Design Conditions

A rough surface damping contact model and its application in spatial variable stator vane mechanism with dry friction joint

Computational Finite Element Analysis of Adaptive Gas Turbine Stator-Rotor Flow Interactions for Future Vertical Lift Propulsion

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