Integral refilmer lip for floatwall panels

Patent · Tue Mar 31 04:00:00 EST 1987

OSTI ID:6608101

Reynolds, H G

This patent describes a liner for a combustor of a gas turbine engine having a generally cylindrically shaped shell and spaced co-extensive panels extending circumferentially and axially relative to the shell, the shell having an outer surface being exposed to cooler air and the panels each having an inner surface being exposed to combustion gases. The shell is bent radially inwardly to define a bend and forms a reduced diameter portion. The upstream and downstream ends of adjacent axial panels are mounted adjacent the bend. At least one combustion/dilution air hole is formed integrally in one of the panels and has a cup portion radially extending through an opening in the shell. The cup has a lip extending radially and axially circumscribing 180/sup 0/ disposed adjacent the inner surface and has an inner diameter having a smaller diameter than the diameter of the combustion/dilution hole in the cup so that the inner diameter projects in the stream of the combustion/dilution air passing through the combustion/dilution air hole and diverts a portion of the dilution/combustion air to flow along the lip to form a cooling film stream directed to flow adjacent the inner surface of the panel.

• Assignee: United Technologies Corp., Hartford, CT
• Patent Number(s): US 4653279
• OSTI ID: 6608101
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
AIR FLOW
CHEMICAL REACTIONS
COMBUSTION
DILUTION
ENGINES
EXHAUST GASES
FLUID FLOW
FLUIDS
GAS FLOW
GAS TURBINE ENGINES
GASEOUS WASTES
GASES
HEAT ENGINES
INCIDENCE ANGLE
INTERNAL COMBUSTION ENGINES
LINERS
OXIDATION
PANELS
SPACE DEPENDENCE
SURFACES
THERMOCHEMICAL PROCESSES
WASTES