Seal exit flow discourager

Patent · Tue Jun 15 04:00:00 EDT 1993

OSTI ID:6349736

Plemmons, L W; Wesling, R A

In an axial flow gas turbine engine comprising a compressor for receiving ambient air, a combustor which receives compressed air from said compressor and fuel from a fuel supply, and first and second turbines which receive combustion products produced by said combustor, and further comprising a first annular cavity which receives combustion products produced by said combustor and a second annular cavity surrounding a shaft which receives cooling air from said compressor, said shaft being connected to said second turbine, said first and second annular cavities communicating across a seal, the improvement is described wherein means are provided for diverting the flow of combustion products exiting said seal radially inward to turbulently mix with cooling air flowing through said second annular cavity, wherein said means for diverting produces a more uniform temperature distribution of gases adjacent to said shaft.

• Assignee: General Electric Co., Cincinnati, OH (United States)
• Patent Number(s): A; US 5218816
• Application Number: PPN: US 7-826723
• OSTI ID: 6349736
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
ANNULAR SPACE
CAVITIES
COMBUSTION PRODUCTS
COMBUSTORS
COMPRESSORS
CONFIGURATION
ENGINES
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINE PARTS
MECHANICAL SHAFTS
SEALS
SHAFTS
SPACE
TEMPERATURE DISTRIBUTION