Patent ID: 11859818
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 11:
12. A system, comprising:
a combustor liner disposed about a combustion chamber of a combustor of a gas turbine system, wherein the combustor is configured to surround an aft end portion of the combustor liner with an upstream end portion of a transition piece, the combustor is configured to surround the combustor liner and the transition piece with a flow sleeve to define an intermediate flow passage, the intermediate flow passage is configured to direct a flow in an upstream direction relative to a downstream direction of a main flow of combustion gas through the combustor, and the aft end portion of the combustor liner comprises:
an inner wall portion exposed to the combustion chamber;
an outer wall portion disposed about the inner wall portion, wherein the outer wall portion terminates at an upstream axial terminal end relative to a coolant flow along the combustor liner; and
a plurality of channels between the inner and outer wall portions of the combustor liner, wherein each channel of the plurality of channels is configured to direct the coolant flow in a flow direction along the combustor liner to convectively cool the combustor liner, wherein each channel of the plurality of channels comprises a microchannel having a cross-sectional area of less than or equal to approximately 6.45 square millimeters, wherein the cross-sectional area of each channel of the plurality of channels decreases in the flow direction from an inlet to an outlet of each channel of the plurality of channels, the inlet of each channel of the plurality of channels is disposed at the upstream axial terminal end of the outer wall portion, each channel of the plurality of channels intakes the coolant flow only in an axial direction via the inlet of the respective channel, the inner and outer wall portions define the plurality of channels between respective inlets and outlets of the plurality of channels, and the outer wall portion comprises a pre-sintered preform (PSP) sheet bonded to the inner wall portion via a thermally conductive bond along an entire axial length of the PSP sheet between the plurality of channels, wherein the plurality of channels are configured as
each channel of the plurality of channels is recessed into a radially inner surface of the outer wall portion, wherein the inlet of each channel of the plurality of channels is disposed at the upstream axial terminal end of the outer wall portion, and each channel of the plurality of channels extends axially downstream of the inlet at a radial depth less than a radial thickness of the outer wall portion;

an inlet guide disposed directly upstream from the inlets of the plurality of channels and the upstream axial terminal end of the outer wall portion, wherein the inlet guide comprises:
a ramp in the inner wall portion of the combustor liner and extending circumferentially about a central axis of the combustor liner about an entire circumference of the combustor liner, wherein the ramp comprises an angled surface having an angle defined by a decreasing thickness of the inner wall portion from a first thickness to a second thickness in the downstream direction toward the inlets of the plurality of channels; and
an opening extending circumferentially about the entire circumference of the combustor liner along the ramp within the intermediate flow passage between the combustor liner and the flow sleeve;

wherein the combustor excludes radial impingement openings directed radially inward toward a flow path of the coolant flow over an axial distance along the ramp, into the inlets, and through the plurality of channels,
wherein the ramp is formed directly in the inner wall portion of the combustor liner adjacent the inlets,
wherein a surface of the inner wall portion facing the combustion chamber is at a single, constant radial distance with respect to the central axis of the combustor liner over the axial distance along the ramp, into the inlets, and through the plurality of channels.