Dual-walled components for a gas turbine engine
An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.
1. A dual-walled component for a gas turbine engine, the dual-walled component comprising:
a cold section part comprising an outer surface;
a hot section part positioned over the outer surface of the cold section part; and
a plurality of support structures positioned between and separating the hot section part from the cold section part to define at least one cooling channel therebetween,
wherein a portion of the hot section part and a portion of the plurality of support structures comprises particles of a high-melt metal alloy and a sintered low-melt braze material,
wherein at least a portion of the sintered low-melt braze material of each of the portions of the hot section part and the plurality of support structures is diffused into the particles of the high-melt metal alloy, and
wherein at least a portion of the sintered low-melt braze material of the portion of the plurality of support structures is diffused into the cold section part.
2. The dual-walled component of claim 1 , wherein the portion of plurality of support structures and the portion of the hot section part are formed from a single-piece pre-sintered preform, the plurality of support structures formed along an inner surface of the hot section part.
3. The dual-walled component of claim 1 , wherein the portion of the hot section part is formed from a pre-sintered preform through heat processing to bond the hot section part to the cold section part through diffusion bonding.
4. The dual-walled component of claim 1 , wherein the portion of the hot section part and the portion of the plurality of support structures each comprise a homogenous mixture of the high-melt metal alloy and the low-melt braze material.
5. The dual-walled component of claim 1 , wherein the high-melt metal alloy of each of the portions has a melting point temperature greater than about 1315° C.
6. The dual-walled component of claim 1 , wherein the low-melt braze material of each of the portions has a melting point temperature less than about 1232° C.
7. The dual-walled component of claim 1 , wherein the low-melt braze material of each of the portions has a melting point temperature between about 1093° C. and about 1260° C.
8. The dual-walled component of claim 1 ,
wherein the low-melt braze material of each of the portions comprises about 40 wt. % to about 50 wt. % of the hot section part, and
wherein the high-melt metal alloy of each of the portions comprises about 50 wt. % to about 60 wt. % of the hot section part.
9. The dual-walled component of claim 1 , wherein the portion of the hot section part comprises an entirety of the hot section part.
10. The dual-walled component of claim 1 , further comprising a support layer, wherein the support layer comprises a base layer and the plurality of support structures extending from an inner surface of the base layer.
11. The dual-walled component of claim 1 ,
wherein the portion of the hot section part and the portion of the plurality of support structures comprises a sintered repair patch, and
wherein the sintered repair patch comprises a replacement hot section part bonded to a second portion of the hot section part and one or more replacement support structures bonded to the cold section part.
12. The dual-walled component of claim 11 , wherein the second portion of the hot section part comprises particles of a high-melt metal alloy and a low-melt braze material.
13. The dual-walled component of claim 12 , wherein the low-melt braze material of the second portion of the hot section part is different from the low-melt braze material of the sintered repair patch.
14. The dual-walled component of claim 1 , wherein an outer surface of the cold section part defines a plurality of impingement apertures that extend between the at least one cooling channel and a cooling plenum.
15. The dual-walled component of claim 1 , wherein an outer surface of the hot section part defines a plurality of cooling apertures that extend between the at least one cooling channel and a heated gas environment.
16. The dual-walled component of claim 1 ,
wherein an outer surface of the hot section part is configured to contact a heated gas environment, and
wherein an outer surface of the cold section part is configured to contact a cooling air plenum, opposite the heated gas environment.
17. The dual-walled component of claim 1 , wherein the cold section part comprises a casted metal alloy.
18. The dual-walled component of claim 1 , wherein the high-melt metal alloy of each of the portions comprises at least one of a Ni-superalloy, Co-superalloy, or a Fe-superalloy.
19. The dual-walled component of claim 1 , wherein the dual-walled component comprises a flame tube, a combustion ring, a combustor casing, a combustor guide vane, a turbine vane, a turbine disc, or a turbine blade.
20. The dual-walled component of claim 1 ,
wherein the cold section part comprises a spar of an airfoil, and
wherein the hot section part and the plurality of support structures comprise a coversheet bonded to the spar.