A blade outer air seal used in a gas turbine engine, the BOAS including a metering plate with metering holes and an impingement plate with impingement holes, the metering plate and impingement plate forming a plurality of separate diffusion cavities forming a grid. A porous metallic plate is bonded
A blade outer air seal used in a gas turbine engine, the BOAS including a metering plate with metering holes and an impingement plate with impingement holes, the metering plate and impingement plate forming a plurality of separate diffusion cavities forming a grid. A porous metallic plate is bonded to the underside of the impingement plate and has a plurality of cooling channels extending from the leading edge to the trailing edge of the BOAS. Cooling air from the blade ring carrier is metered through the metering holes and into the diffusion cavities, and then passes through a plurality of impingement holes and into a cooling channel, to be discharged out the trailing edge side of the BOAS. Inter-segment cooling holes also pass cooling air out to the sides of the BOAS.
대표청구항▼
I claim the following: 1. A blade outer air seal for use in a gas turbine engine, the blade outer air seal comprising: a plurality of diffusion cavities each having a metering hole in fluid communication with a cooling air supply; an impingement hole plate having a plurality of impingement holes in
I claim the following: 1. A blade outer air seal for use in a gas turbine engine, the blade outer air seal comprising: a plurality of diffusion cavities each having a metering hole in fluid communication with a cooling air supply; an impingement hole plate having a plurality of impingement holes in fluid communication with the diffusion cavities; a porous metallic plate having a plurality of cooling channels formed therein; and, a thermal barrier coating applied to the outer surface of the porous metallic plate; wherein cooling air passes through the metering holes and into the diffusion cavities, and then through at least one of the impingement holes and into the cooling channel to provide cooling to the blade outer air seal. 2. The blade outer air seal of claim 1, and further comprising: the cooling channels in the porous metallic plate extend substantially in a direction of the hot gas flow through the turbine; and, each channel includes a plurality of impingement holes in fluid communication with a diffusion cavity. 3. The blade outer air seal of claim 1, and further comprising: a plurality of diffusion cavities forming a compartment of cavities, each compartment diffusion cavity being separated from other compartment cavities by stiffener ribs. 4. The blade outer air seal of claim 3, and further comprising: two compartment cavities extend from the leading edge to the trailing edge of the blade outer air seal; and, four compartment cavities extend from side to side of the blade outer air seal. 5. The blade outer air seal of claim 1, and further comprising: each of the sides of the blade outer air seal includes a plurality of inter-segment cooling holes in fluid communication with the outer-most cooling channels to discharge cooling air from the blade outer air seal and onto an adjacent blade outer air seal. 6. The blade outer air seal of claim 1, and further comprising: the porous metallic plate is porous enough to allow for cooling air from the channel to flow through the porous metal and out through a hole resulting from a spallation occurring in the TBC. 7. The blade outer air seal of claim 2, and further comprising: a plurality of diffusion cavities forming a compartment of cavities, each compartment diffusion cavity being separated from other compartment cavities by stiffener ribs. 8. The blade outer air seal of claim 7, and further comprising: two compartment cavities extend from the leading edge to the trailing edge of the blade outer air seal; and, four compartment cavities extend from side to side of the blade outer air seal. 9. The blade outer air seal of claim 3, and further comprising: each of the sides of the blade outer air seal includes a plurality of inter-segment cooling holes in fluid communication with the outer-most cooling channels to discharge cooling air from the blade outer air seal and onto an adjacent blade outer air seal. 10. The blade outer air seal of claim 8, and further comprising: the porous metallic plate is porous enough to allow for cooling air from the channel to flow through the porous metal and out through a hole resulting from a spallation occurring in the TBC. 11. A gas turbine engine having a turbine section with at least one stage of rotor blades, each blade having a blade tip that forms a gap with a blade outer air seal secured to a stationary casing, the blade outer air seal comprising: a metering cover plate having a plurality of metering holes therein; an impingement and stiffener rib plate having a plurality of impingement holes therein; the metering cover plate and the impingement and stiffener plate forming a plurality of diffusion cavities; a porous metallic plate having a plurality of cooling channels, the porous metallic plate being secured to the impingement plate such that the impingement holes are aligned with the cooling channels; and, a TBC applied on the porous metallic plate on the side opposite to the cooling channels. 12. The gas turbine engine of claim 11, and further comprising: the plurality of diffusion cavities are formed as separate compartment cavities such that a plurality of compartment cavities extend along the blade outer air seal in a direction parallel to the flow through the turbine and a plurality of compartment cavities extend along the blade outer air seal in a direction normal to the flow through the turbine; and, each compartment cavity being separated from other cavities and in fluid communication to a cooling air supply though a single metering hole. 13. The gas turbine engine of claim 12, and further comprising: the cooling channels in the porous metallic plate extend in a direction substantially parallel top the gas flow through the turbine. 14. The gas turbine engine of claim 13, and further comprising: each of the compartment cavities includes a plurality of impingement holes in fluid communication with a cooling channel. 15. The gas turbine engine of claim 11, and further comprising: the porous metallic plate is of such porosity that when a piece of the TBC spalls off and leaves an opening, cooling air from the cooling channel flows out through the opening to provide transpiration cooling to the TBC. 16. The gas turbine engine of claim 14, and further comprising: each of the two sides of the blade outer air seal includes a plurality of inter-segment cooling holes in fluid communication with the outer-most cooling channel to provide cooling to the side of the blade outer air seal. 17. A process for cooling a blade outer air seal used in a gas turbine engine, the process comprising the steps of: supplying compressed cooling air to a blade ring carrier of the engine; metering the cooling air into a plurality of separate diffusion cavities formed within the blade out air seal; impinging cooling from the diffusion cavities into cooling channels extending along the blade outer air seal; and, discharging the cooling air from the cooling channels out the trailing edge side of the blade outer air seal. 18. The process for cooling a blade outer air seal of claim 17, and further comprising the step of: metering the cooling air into a plurality of diffusion compartments extending in both directions of the blade air outer seal. 19. The process for cooling a blade outer air seal of claim 18, and further comprising the step of: channeling the cooling air through the cooling channels in a direction along the blade outer air seal from the leading edge to the trailing edge. 20. The process for cooling a blade outer air seal of claim 19, and further comprising the step of: passing cooling air from the individual compartment cavities through a plurality of impingement holes into the cooling channels such that cooling air through one metering hole flows through a plurality of impingement holes and into a single cooling channel.
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