Research Papers: Gas Turbines: Structures and Dynamics

Dynamic Response of a Metal and a CMC Turbine Blade During a Controlled Rub Event Using a Segmented Shroud

[+] Author and Article Information
Nisrene Langenbrunner, Matt Weaver

GE Aviation,
Cincinnati, OH 45215

Michael G. Dunn

Gas Turbine Laboratory,
Ohio State University,
Columbus, OH 43235
e-mail: dunn.129@osu.edu

Corso Padova, Jeffery Barton

Gas Turbine Laboratory,
Ohio State University,
Columbus, OH 43235

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 30, 2014; final manuscript received September 2, 2014; published online December 9, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(6), 062504 (Jun 01, 2015) (8 pages) Paper No: GTP-14-1449; doi: 10.1115/1.4028685 History: Received July 30, 2014; Revised September 02, 2014; Online December 09, 2014

Ceramic matrix composites (CMCs) provide several benefits over metal blades including weight and increased temperature capability, and have the potential for increased engine performance by reduction of the cooling flow bled from the compressor and by allowing engines to run at higher turbine inlet temperatures. These CMC blades must be capable of surviving fatigue (high cycle and low cycle), creep, impact, and any tip rub events due to the engine missions or maneuvers that temporarily close blade tip/shroud clearances. As part of a cooperative research program between GE Aviation and the Ohio State University Gas Turbine Laboratory, OSU GTL, the response of a CMC stage 1 low-pressure turbine blade has been compared with the response of an equivalent metal turbine blade using the OSU GTL large spin-pit facility (LSPF) as the test vehicle. Load cells mounted on the casing wall, strain gages mounted on the airfoils, and other instrumentation are used to assess blade tip rub interactions with a 120-deg sector of a representative turbine stationary casing. The intent of this paper is to present the dynamic response of both the CMC and the metal blades with the turbine disk operating at design speed and with representative incursion rates and depths. Casing wear and blade tip wear are both characterized for several types of rub conditions including a light, medium, and heavy rub at room temperature. For each condition, the rub primary dynamic modes have been evaluated, and the corresponding blade tip loads have been calculated. The preliminary results suggest that a CMC blade has similar abilities to a metal blade during a rub event.

Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Fig. 1

Tip rub rig schematic

Grahic Jump Location
Fig. 2

Typical incursion motion with BCS

Grahic Jump Location
Fig. 3

Typical x-direction load cell response with the BCS

Grahic Jump Location
Fig. 4

Load cell measurement axis (metal blade shown)

Grahic Jump Location
Fig. 5

Segmented shoe wear scar for blade light rub condition

Grahic Jump Location
Fig. 6

Precision micrometer within the LSPF

Grahic Jump Location
Fig. 7

Blade tip wear comparisons of metal and CMC

Grahic Jump Location
Fig. 8

Filtering system noise

Grahic Jump Location
Fig. 9

Torque zones for force estimation

Grahic Jump Location
Fig. 10

Comparing max load cell factors for both blades in the radial and tangential directions

Grahic Jump Location
Fig. 11

Light rub strain gage frequency decomposition

Grahic Jump Location
Fig. 12

Medium rub 1F content for both blades




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