GAS TURBINE ENGINE WITH SEALING SURFACE FOR BLADE OUTER AIR SEAL
FIG2 is a schematic view of a known turbine section
FIG2 shows a turbine section 100. A turbine blade 102 has a radially outer extent 103. A BOAS 104 is positioned radially outward of the tip 103. The BOAS 104 has a forward hook 106 and an aft hook 108. A support or attachment block 110 has surfaces 112 and 114 supporting the hooks 106 and 108. The attachment block 110 further has forward mount portion 115 and aft mount portion 116 mounting the attachment block and, hence the BOAS 104, into static structure 118. The structure as generally shown in FIG2 is known. It is desirable to prevent leakage at the forward end from moving radially outwardly in the direction of the arrow L.
schematic view
121
static vane
126
inwardly extending lip inwardly extending flange
104
BOAS
112
has surfaces
118
static structure
115
portion
108
aft hook hooks hook
36
engine static structure
120
vane support
103
radially outer extent tip
30
low speed spool
116
aft mount portion
10
feet
129
radially outermost extent
128
seal
134
straight portion
110
attachment block
107
curved portion
124
outer seal attachment portion
139
aft end
100
turbine section
102
blade
106
hook hooks
114
has surfaces
127
radially innermost extent
['1. A gas turbine engine (20) comprising: a turbine section (28; 100) having a turbine rotor and at least one blade (102) extending outwardly of said turbine rotor, said turbine rotor rotating about an axis of rotation (A); a blade outer air seal (104) positioned radially outward of said at least one blade (102), said blade outer air seal (104) having an axially forward hook (106) and an axially aft hook (108) supported to a static structure (118); an axial seal (122, 128; 222) attached to said static structure (118) forward of said forward hook (106), and having a sealing portion extending in an aft direction; and a sealing surface member (130; 230) positioned intermediate an aft end (139) of said axial seal (122, 128; 222) and a forward end of said forward hook (106) to provide a sealing surface for sealing between said axial seal (122, 128; 222) and said blade outer air seal (104).', '3. The gas turbine engine (20) as set forth in claim 1 or 2, wherein said forward hook (106) has a curved portion (107) extending from a blade outer air seal body into said forward hook (106), and said axial seal (122, 128; 222) is radially aligned with said curved portion (107) such that said sealing surface member (130; 230) provides a sealing surface in place of said curved portion (107).', '10. The gas turbine engine (20) as set forth in any preceding claim, wherein said axial seal (122, 128; 222) is supported on a vane support (120) which is located forward of said blade (102).', '12. The gas turbine engine (20) as set forth in claim 11, wherein said radially inwardly extending ledge (126) has a radially innermost extent (127) which is radially inward of a radially outermost extent of a forward end (129) of said curved portion (136) of said seal surface member (130).']