Title:
SEAL ASSEMBLY IN A GAS TURBINE ENGINE INCLUDING GROOVES IN A RADIALLY OUTWARDLY FACING SIDE OF A PLATFORM AND IN A INWARDLY FACING SIDE OF AN INNER SHROUD
Document Type and Number:
WIPO Patent Application WO/2014/143413
Kind Code:
A3
Abstract:
A seal assembly (50) between a disc cavity and a turbine section (26) hot gas path includes a stationary vane assembly (12) with an inner shroud (16) and a rotating blade assembly (18) downstream from the vane assembly and including a plurality of blades that are supported on a platform (28) and rotate with a turbine rotor and the platform during operation of the engine. The inner shroud (16) comprises a radially innwardly facing suface (46) comprising vane grooves (60), and the platform includes a radially and axially facing surface (146), and a plurality of grooves (160) extending into the said surface. The grooves (60, 160) are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.
Inventors:
LEE CHING-PANG (US)
Application Number:
PCT/US2014/012525
Publication Date:
December 18, 2014
Filing Date:
January 22, 2014
Export Citation:
Assignee:
SIEMENS AG (DE)
LEE CHING-PANG (US)
LEE CHING-PANG (US)
International Classes:
F01D11/00; F01D5/08; F01D11/04
Foreign References:
| US20100074734A1 | 2010-03-25 | |||
| US20060269399A1 | 2006-11-30 | |||
| EP1582697A1 | 2005-10-05 | |||
| US20110067414A1 | 2011-03-24 |
Attorney, Agent or Firm:
SWANSON, Erik C. et al. (170 Wood Avenue SouthIselin, New Jersey, US)
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