0
Research Papers

Heterogeneous Optimization Strategies for Carved and Squealer-Like Turbine Blade Tips

[+] Author and Article Information
C. De Maesschalck

von Karman Institute for Fluid Dynamics,
Rhode Saint Genèse,
Brussels BE-1640, Belgium
e-mail: cis.demaesschalck@gmail.com

S. Lavagnoli

von Karman Institute for Fluid Dynamics,
Rhode Saint Genèse,
Brussels BE-1640, Belgium
e-mail: lavagnoli@vki.ac.be

G. Paniagua

von Karman Institute for Fluid Dynamics,
Rhode Saint Genèse,
Brussels BE-1640, Belgium
e-mail: gpaniagua@me.com

T. Verstraete

von Karman Institute for Fluid Dynamics,
Rhode Saint Genèse,
Brussels BE-1640, Belgium
e-mail: tom.verstraete@vki.ac.be

R. Olive

Safran—Snecma,
Villaroche 77550, France
e-mail: remi.olive@snecma.fr

P. Picot

Safran—Snecma,
Villaroche 77550, France
e-mail: philippe.picot@snecma.fr

1Corresponding author.

2Present address: Zucrow Laboratories, Purdue University, 500 Allison Road, West Lafayette, IN 47907.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 15, 2015; final manuscript received March 2, 2016; published online July 27, 2016. Assoc. Editor: Jim Downs.

J. Turbomach 138(12), 121011 (Jul 27, 2016) (12 pages) Paper No: TURBO-15-1260; doi: 10.1115/1.4033975 History: Received November 15, 2015; Revised March 02, 2016

Superior rotor tip geometries possess the potential to simultaneously mitigate aerodynamic losses and severe thermal loads onto the rotor overtip region. However, classical design strategies are usually constrained to a specific type of geometry, narrowing the spread of shape topologies considered during the design phase. The current paper presents two novel multi-objective optimization methodologies that enable the exploration of a broad range of distinct tip configurations for unshrouded rotor blades. The first methodology is a shape optimization process that creates a fully carved blade tip shape defined through a Bezier surface controlled by 40 parameters. Combined with a differential evolution (DE) optimization strategy, this approach is applied to a rotor blade for two tip gap sizes: 0.85% (tight) and 1.38% (design) of the blade span. The second methodology is based on a topology optimization process that targets the creation of arbitrary tip shapes comprising one or multiple rims with a fixed height. The tip section of the blade has been divided into more than 200 separate zones, where each zone can be either part of an upstanding rim or part of the cavity floor. This methodology was tested with a level-set approach in combination with a DE optimizer and coupled to an optimization routine based on genetic algorithms (GAs). The current study was carried out on a modern high-pressure turbine operating at engine-like Reynolds and high subsonic outlet Mach numbers. A fully hexahedral unstructured mesh was used to discretize the fluid domain. The aerothermal performance of each tip profile was evaluated accurately through Reynolds-averaged Navier–Stokes (RANS) simulations adopting the shear-stress transport (SST) turbulence model. Multi-objective optimizations were set for both design strategies that target higher aerodynamic rotor efficiencies and simultaneous minimization of the heat load. This paper illustrates a wide variety of profiles obtained throughout the optimization and compares the performance of the different strategies. The research shows the potential of such novel methodologies to reach new unexplored types of blade tip designs with enhanced aerothermal performances.

Copyright © 2016 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Computational domain

Grahic Jump Location
Fig. 2

Grid sensitivity analysis: (a) effect on rotor efficiency and (b) effect on tip heat transfer

Grahic Jump Location
Fig. 3

Cooled turbine tip geometry for the solver validation (a) and hexahedral mesh (b)

Grahic Jump Location
Fig. 4

Aerodynamic validation of the blade loading (a) and overtip casing pressure distribution (b)

Grahic Jump Location
Fig. 5

Validation of the heat transfer on the tip cavity floor (a) and overtip casing (b)

Grahic Jump Location
Fig. 6

Illustration of the carved tip parametrization

Grahic Jump Location
Fig. 7

Block discretization for the squealer-like optimization: (a) block discretization pattern and (b) graphical example of the block-up/block-down tip surface generation

Grahic Jump Location
Fig. 8

Binary and level-set approach for the squealer-like optimization

Grahic Jump Location
Fig. 9

Flowchart of the optimization methodology

Grahic Jump Location
Fig. 10

Strategy sequence for the carved tip optimization

Grahic Jump Location
Fig. 11

Strategy sequence for the squealer-like optimization

Grahic Jump Location
Fig. 12

The Pareto front for the carved tip optimization at design and tight clearance

Grahic Jump Location
Fig. 13

Convergence evolution of the optimization objectives for the tight clearance ((a) and (b)) and design clearance ((c) and (d))

Grahic Jump Location
Fig. 14

Zoom on the carved optimization Pareto front (a) and a detailed view of four optimal shapes (b)

Grahic Jump Location
Fig. 15

The Pareto front for the squealer-like optimizations

Grahic Jump Location
Fig. 16

Blade torque versus the massflow for every evaluated profile

Grahic Jump Location
Fig. 17

Downstream vorticity in the upper 50% of the blade span against the efficiency

Grahic Jump Location
Fig. 18

Total tip heat transfer (W) versus the surface-averaged tip heat load (W/m2)

Grahic Jump Location
Fig. 19

Tip heat transfer (W) in function of the heat load RMS value

Grahic Jump Location
Fig. 20

Heat transfer to the SS and PS for the upper 25% and the full blade span

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In