Design Innovation Papers

Aerodynamic Optimization of High-Pressure Turbines for Lean-Burn Combustion System

[+] Author and Article Information
Shahrokh Shahpar

e-mail: Shahrokh.Shahpar@Rolls-Royce.com

Stefano Caloni

e-mail: Stefano.Caloni@Rolls-Royce.com
CFD Methods, Design System Engineering,
Rolls-Royce plc,
Derby DE24 8BJ, UK

Contributed by the Turbomachinery Committee of ASME for publication in the Journal of Engineering for Gas Turbines and Power. Manuscript received October 3, 2012; final manuscript received October 25, 2012; published online April 23, 2013. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(5), 055001 (Apr 23, 2013) (11 pages) Paper No: GTP-12-1388; doi: 10.1115/1.4007977 History: Received October 03, 2012; Revised October 25, 2012

Modern lean-burn combustors make use of high flow swirl to maintain flame stability. The swirling flow can persist downstream of the turbine first vane, changing the loading on the rotor, leading to a reduction in efficiency. This paper presents the results of an automatic optimization study carried out to mitigate the effect of high swirling flow on a high pressure turbine stage. A high-fidelity computational fluid dynamics (CFD)-based design optimization using a multipoint approximation (response surface) method is carried out to produce a new vane and a new rotor configuration with a significantly improved aerodynamic performance. It is demonstrated that the novel optimization methodology can cope well with a number of near equality constraints needed for a practical design.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Fig. 3

SILOET turbine stage geometry (ST1)

Grahic Jump Location
Fig. 4

PADRAM multiblock mesh for the (a) NGV and (b) rotor, (c) detailed close-up of the NGV trailing edge and (d) rotor TE

Grahic Jump Location
Fig. 5

PADRAM high stagger mesh topology

Grahic Jump Location
Fig. 6

Vane and rotor radial positions where the design modifications are applied

Grahic Jump Location
Fig. 2

Schematic of zooming of trust regions in MAM

Grahic Jump Location
Fig. 1

Optimization loop using the SOPHY system

Grahic Jump Location
Fig. 7

Skew parameter effect on the blade geometry, radial distribution of the design parameter (on the left), original shape (in the middle), the modified shape (on the right)

Grahic Jump Location
Fig. 8

Sweep applied to the vane geometry

Grahic Jump Location
Fig. 9

Lean applied to the vane geometry

Grahic Jump Location
Fig. 10

PADRAM recambering at the LE and TE

Grahic Jump Location
Fig. 17

Optimum NGV shape superimposed on the datum

Grahic Jump Location
Fig. 16

The MAM optimization history—no Hydra-PADRAM failure in the whole optimization

Grahic Jump Location
Fig. 11

Film cooling rows and TE coolant slot on the original and the modified blade

Grahic Jump Location
Fig. 12

Gas turbine engine scheme

Grahic Jump Location
Fig. 13

SILOET inlet boundary conditions—vane LE positions shown by dash lines

Grahic Jump Location
Fig. 14

Streamlines for uniform condition (on the left) and with swirl boundary condition (on the right)

Grahic Jump Location
Fig. 15

Loading of NGVs with uniform and swirl inlet conditions

Grahic Jump Location
Fig. 18

Static pressure distributions for the datum and optimum vane sections

Grahic Jump Location
Fig. 19

Radial distribution of the axial and tangential velocities at the vane exit plane

Grahic Jump Location
Fig. 20

Contours of axial velocity (datum design on the left, optimum on the right)

Grahic Jump Location
Fig. 21

CPL difference between baseline and optimum

Grahic Jump Location
Fig. 22

Shape of the optimized rotor, LE and TE views

Grahic Jump Location
Fig. 23

Static pressure distributions for the datum and optimum rotor blade sections

Grahic Jump Location
Fig. 24

Entropy contour at 95% span of rotor blade (datum is shown on left, optimized blade on the right)




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