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Research Papers

State-of-the-Art Cooling Technology for a Turbine Rotor Blade

[+] Author and Article Information
Jason Town

Applied Research Lab,
Pennsylvania State University,
College Park, PA 16802
e-mail: jet234@psu.edu

Douglas Straub

National Energy Technology Laboratory,
Morgantown, WV 26505
e-mail: douglas.straub@netl.doe.gov

James Black

National Energy Technology Laboratory,
Pittsburgh, PA 15236
e-mail: james.black@netl.doe.gov

Karen A. Thole

Mechanical and Nuclear Engineering Department,
Pennsylvania State University,
College Park, PA 16802
e-mail: kthole@engr.psu.edu

Tom I-P. Shih

School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907
e-mail: tomshih@purdue.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received March 2, 2018; final manuscript received March 26, 2018; published online June 14, 2018. Editor: Kenneth Hall.

J. Turbomach 140(7), 071007 (Jun 14, 2018) (12 pages) Paper No: TURBO-18-1049; doi: 10.1115/1.4039942 History: Received March 02, 2018; Revised March 26, 2018

Effective internal and external cooling of airfoils is key to maintaining component life for efficient gas turbines. Cooling designs have spanned the range from simple internal convective channels to more advanced double-walls with shaped film-cooling holes. This paper describes the development of an internal and external cooling concept for a state-of-the-art cooled turbine blade. These cooling concepts are based on a review of literature and patents, as well as, interactions with academic and industry turbine cooling experts. The cooling configuration selected and described in this paper is referred to as the “baseline” design, since this design will simultaneously be tested with other more advanced blade cooling designs in a rotating turbine test facility using a “rainbow turbine wheel” configuration. For the baseline design, the leading edge is cooled by internal jet impingement and showerhead film cooling. The midchord region of the blade contains a three-pass serpentine passage with internal discrete V-shaped trip strips to enhance the internal heat transfer coefficient (HTC). The film cooling along the midchord of the blade uses multiple rows of shaped diffusion holes. The trailing edge is internally cooled using jet impingement and externally film cooled through partitioned cuts on the pressure side of the blade.

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Figures

Grahic Jump Location
Fig. 1

Overall cooling effectiveness as a function of the HLP (without film cooling) based on Eq. (1)

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Fig. 2

Overall cooling effectiveness as a function of HLP including adiabatic film cooling effectiveness

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Fig. 3

General thermal resistance model for a turbine blade with film-cooling

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Fig. 4

Impact of 1D model parameters on the overall cooling effectiveness

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Fig. 5

Proposed baseline blade cooling design (view from the tip toward the hub)

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Fig. 6

Showerhead cooling design previously presented in the literature [10]

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Fig. 7

Internal cooling design with dedicated leading and trailing edge supply and five pass serpentine [18]

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Fig. 8

Bifurcated blade with serpentine passage design [20]

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Fig. 9

Thermal performance in rotating channels [25]

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Fig. 10

Diffused 7-7-7 film-cooling hole geometry [7]

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Fig. 11

Adiabatic effectiveness for a diffused 7-7-7 film cooling hole compared to other designs noting laidback angle [7]

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Fig. 12

Internal trailing edge cooling patents: (a) impingement to fully bridged pin fin [30], (b) double impingement to fully bridged pin fin [31], (c) pressure side angled impingement/rib turbulators [32], (d) pressure side angled race track impingement onto skewed rib turbulators [33], (e) triple impingement [34], and (f) triple impingement with rib turbulators [35]

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Fig. 13

Angled racetrack holes with and without heat transfer enhancement devices [36,37]

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Fig. 14

Various trailing edge designs [41]

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Fig. 15

Film effectiveness along inner suction surface for letterbox partitions and gill slot trailing edge designs [43]

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Fig. 16

Effects of partition taper on downstream film effectiveness [45]

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Fig. 17

Trailing edge design modifications [46]

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Fig. 18

Film effectiveness of various trailing edge designs [46]

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Fig. 19

Proposed trailing edge design for baseline

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