0
Research Papers

Recent Advances of Internal Cooling Techniques for Gas Turbine Airfoils

[+] Author and Article Information
Minking K. Chyu

e-mail: mkchyu@pitt.edu

Sin Chien Siw

Department of Mechanical Engineering and Materials Science,
University of Pittsburgh,
Pittsburgh, PA 15261

1Corresponding author.

Manuscript received November 5, 2012; final manuscript received February 5, 2013; published online May 17, 2013. Assoc. Editor: Srinath V. Ekkad.

J. Thermal Sci. Eng. Appl 5(2), 021008 (May 17, 2013) (12 pages) Paper No: TSEA-12-1197; doi: 10.1115/1.4023829 History: Received November 05, 2012; Revised February 05, 2013

The performance goal of modern gas turbine engines, both land-base and air-breathing engines, can be achieved by increasing the turbine inlet temperature (TIT). The level of TIT in the near future can reach as high as 1700 °C for utility turbines and over 1900 °C for advanced military engines. Advanced and innovative cooling techniques become one of the crucial major elements supporting the development of modern gas turbines, both land-based and air-breathing engines with continual increment of turbine inlet temperature (TIT) in order to meet higher energy demand and efficiency. This paper discusses state-of-the-art airfoil cooling techniques that are mainly applicable in the mainbody and trailing edge section of turbine airfoil. Potential internal cooling designs for near-term applications based on current manufacturing capabilities are identified. A literature survey focusing primarily on the past four to five years has also been performed.

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

References

Figures

Grahic Jump Location
Fig. 1

Projected coal-gas turbine operating parameters [2-4]

Grahic Jump Location
Fig. 2

Schematic of typical gas turbine airfoil with common cooling techniques [6]

Grahic Jump Location
Fig. 3

Airfoil with double-wall cooling [8-11]

Grahic Jump Location
Fig. 4

Generic Lamilloy® cooling [12]

Grahic Jump Location
Fig. 5

Durability map illustrating the path for higher cooling effectiveness [16]

Grahic Jump Location
Fig. 6

Local heat transfer coefficient (W/m2-K) and CFD simulated streakline in a double-wall cooling channel, channel's Reynolds number = 8000 [17]

Grahic Jump Location
Fig. 7

Rib-turbulators for internal cooling passages in turbine airfoil [21]

Grahic Jump Location
Fig. 8

Local heat transfer coefficient distribution with diamond shaped pin-fins [44]

Grahic Jump Location
Fig. 9

Top view of test plate with different pin-fin configurations

Grahic Jump Location
Fig. 10

Local heat transfer coefficient distribution (case 1)

Grahic Jump Location
Fig. 11

Endwall heat transfer enhancement versus Re

Grahic Jump Location
Fig. 12

Total heat transfer enhancement versus Re

Grahic Jump Location
Fig. 13

Different dimple geometries [60-62]

Grahic Jump Location
Fig. 14

Heat transfer enhancement versus Re with dimples

Grahic Jump Location
Fig. 15

Innovative cooling configurations with mesh and dimple [64]

Grahic Jump Location
Fig. 16

Schematic layout of detached pin-fin with broken rib and full rib

Grahic Jump Location
Fig. 17

Local heat transfer coefficient, h (W/m2-K) distribution for endwall and pin-fins [68]

Grahic Jump Location
Fig. 18

Total heat transfer enhancement of detached pin-fins with broken rib and full rib [68]

Grahic Jump Location
Fig. 19

Heat transfer enhancement of pin-fins with dimples and rib-turbulators

Grahic Jump Location
Fig. 20

Zig-zag channel with different surface configuration [70]

Grahic Jump Location
Fig. 21

Local heat transfer coefficient of smooth zig-zag channel [69]

Grahic Jump Location
Fig. 22

Local heat transfer coefficient of rib-turbulated zig-zag channel [70]

Grahic Jump Location
Fig. 23

Total heat transfer enhancement versus Re (zig-zag channel) [70]

Grahic Jump Location
Fig. 24

Pressure loss versus Re (zig-zag channel) [70]

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.

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