GAS TURBINE ENGINE COMPONENT
FIG2 is an enlarged schematic view of a portion of a turbine section
FIG2 illustrates an enlarged schematic view of the high pressure turbine 54, however, other sections of the gas turbine engine 20 could benefit from this disclosure, such as the compressor section 24 or low pressure turbine 46. In the illustrated example, the high pressure turbine 54 includes a one-stage turbine section including a first rotor assembly 60. In another example, the high pressure turbine 54 could include a two-stage high pressure turbine section with multiple rotor assemblies. The forward wall 102, the aft wall 104, the outer wall 106, and the base portion 108 of the BOAS 82 define a passage 110 for accepting a wear liner 112, such as a metallic wear liner. A radially inner side of the base portion 108 at least partially defines the core flow path C and is located adjacent a tip of the airfoil 80 (See FIG2).
enlarged schematic view
80
airfoil airfoils
92
one airfoil two airfoils
96
vane outer platform
64
first disk
66
respective first rim
108
base portion
36
engine static structure
62
first rotor blades
['1. A blade outer air seal (82) comprising: a base portion (108) extending between a leading edge (98) and a trailing edge (100); and a forward wall (102) and an aft wall (104) extending radially outward from the base portion (108) to a radially outer portion (106), wherein the radially outer portion (106) is spaced from the base portion (108).']