Blade outer air seal assembly and support
An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member.
1. A blade outer air seal support assembly, comprising:
a main support member configured to support a blade outer air seal, the main support member extending generally axially between a leading edge portion and a trailing edge portion, the leading edge portion configured to be slidably received within a groove established by the blade outer air seal;
a support tab extending radially inward from the main support member toward the blade outer air seal, the support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal, the entire support tab positioned upstream from the trailing edge portion;
a gusset spanning between the support tab and the main support member;
a main body portion of a blade outer air seal having an outwardly facing surface and an, inwardly facing surface;
an impingement plate secured to the outwardly facing surface;
a plurality of elongated ribs disposed between the impingement plate and the main body portion; and
a plurality of depto warts disposed between the impingement plate and the main body portion, the plurality of depto warts positioned axially closer to a trailing edge portion of the blade outer air seal than the plurality of elongated ribs.
2. The blade outer air seal support assembly of claim 1 , wherein an interface between the gusset and the support tab has an interface length, and a ratio of the interface length to a radial length of the support tab is about 2 to 3.
3. The blade outer air seal support assembly of claim 1 , wherein the main support member includes an extension configured to be received with a groove established within the blade outer air seal, the extension having a radially outwardly facing surface configured to contact a portion of the blade outer air seal to limit radial movement of the blade outer air seal relative to the main support member when the blade outer air seal is in an installed position relative to the main support member.
4. The blade outer air seal support assembly of claim 3 , wherein the groove is established near a leading edge portion of the blade outer air seal.
5. The blade outer air seal support assembly of claim 1 , wherein the support tab is configured to contain a blade during a blade-out event.
6. A blade outer air seal assembly, comprising:
a main body portion having an outwardly facing surface and an inwardly facing surface;
an impingement plate secured to the outwardly facing surface;
a plurality of elongated ribs disposed between the impingement plate and the main body portion; and
a plurality of depto warts disposed between the impingement plate and the main body portion, the plurality of depto warts positioned axially closer to a trailing edge portion of the blade outer air seal than the plurality of elongated ribs.
7. The blade outer air seal assembly of claim 6 , wherein the impingement plate includes a multiple of apertures configured to direct a flow of air toward the plurality of elongated ribs and the depto warts, the multiple of apertures configured to direct more air toward the elongated ribs than the depto warts.
8. The blade outer air seal assembly of claim 6 , wherein the plurality of ribs are axially aligned.
9. The blade outer air seal assembly of claim 6 , wherein the plurality of ribs are cast together with the main body portion.
10. The blade outer air seal assembly of claim 6 , wherein the impingement plate is welded to the main body portion.
11. A method of film cooling utilizing a blade outer air seal comprising:
providing a plurality of depto warts and a plurality of elongated ribs within a cavity between an impingement plate and a main body portion of a blade outer air seal, the plurality of depto warts positioned axially closer to a trailing edge portion of the blade outer air seal than the plurality of elongated ribs;
providing an inwardly facing surface of the blade outer air seal, the inwardly facing surface having a blade path area and a peripheral area different than the blade path area, the entire blade path area and the entire peripheral area being radially aligned; and
directing cooling air from the cavity through a plurality of apertures established in the inwardly facing surface, wherein the plurality of apertures are concentrated in the blade path area.
12. The method of film cooling of claim 11 , including providing the plurality of apertures exclusively within the blade path area.
13. The method of film cooling of claim 11 , wherein the blade path area and the peripheral area are parallel to an axis of a gas turbine engine.