초록 ▼

A modular cooling panel for cooling a turbine member is provided. The cooling panel comprises a first panel having a relative width, relative length, upper surface and lower surface. The upper surface defines at least one corrugated portion traversing along a portion of the relative width of the upp

A modular cooling panel for cooling a turbine member is provided. The cooling panel comprises a first panel having a relative width, relative length, upper surface and lower surface. The upper surface defines at least one corrugated portion traversing along a portion of the relative width of the upper surface. The corrugated portion defines a cooling flow channel through which a cooling fluid can travel to cool the turbine member. The cooling flow channel has at least one inlet opening for enabling the cooling fluid to enter into the cooling flow channel. The lower portion surface of the first panel is adapted to be coupled in fluid communication with the turbine member.

대표청구항 ▼

[ I claim:] [1.] A cooling panel for a gas turbine for enhancing cooling of a segment of a turbine member having a wall with an inner and outer surface, where in operation of the turbine the inner surface of the wall houses a working gas that travels along an axial dimension of the turbine member de

[ I claim:] [1.] A cooling panel for a gas turbine for enhancing cooling of a segment of a turbine member having a wall with an inner and outer surface, where in operation of the turbine the inner surface of the wall houses a working gas that travels along an axial dimension of the turbine member defining its length, which is perpendicular to its width, said cooling panel comprising:a first modular cooling panel having a relative width (W) and Length (L), which are substantially less than a corresponding dimension of the turbine member wall measured along the same line of measurement of the dimension of the cooling panel when the panel is positioned on the turbine member wall, an outer surface and an inner surface, said inner surface of the cooling panel defining at least one channeled portion traversing along a portion of the inner surface of the cooling panel, said channeled portion defining a cooling flow channel through which a cooling fluid can travel to cool the segment of the turbine member, said cooling flow channel having at least one inlet opening extending into the inner surface of the cooling panel for enabling the cooling fluid to enter into the cooling flow channel from a cooling gas plenum in the turbine that extends over at least a portion of the turbine member's wall, said inner surface of the cooling panel having a portion thereof adapted to be removably attached to the outer surface of the turbine member wall in a manner that does not obstruct the inlet opening from being in fluid communication with the cooling gas plenum, and the cooling panel having a closed end, spaced along said cooling flow channel from said inlet opening, to direct the cooling fluid to an outlet opening which is machined through the turbine member's wall and aligned with the cooling channel to permit the cooling fluid to be in fluid communication with the inner surface of the turbine member wall, the first cooling panel being capable of being replaced without materially affecting or requiring disassembly of the wall or requiring the dismantling of any other cooling panel affixed to the outer surface of the wall. [11.] A method of enhancing the cooling properties of a portion of a cooling fluid flow path within a gas turbine transition member enclosed within a shell that surrounds a transition member wall that funnels a working gas to a turbine section to produce mechanical work, wherein the area between the shell and an outer surface on the wall defines the cooling fluid flow path, and the working gas travels within the wall along an axial dimension of the transition member defining its length, which is perpendicular to its width, comprising the steps of:machining a predetermined sized wall port through the surface of the wall, that provides a cooling fluid flow path between the shell and the interior of the wall;positioning a discrete cooling panel on the outer surface of the wall, the cooling panel having a channeled portion that defines an elongated coolant flow channel with a cooling fluid inlet port at one end and a closed end spaced from the inlet port, and the cooling panel occupying an area on the outer surface of the wall that has a width and length which is substantially less than the corresponding dimension of the wall;aligning a portion of the cooling flow channel proximate the closed end with the wall port and the rest of the cooling flow channel with a portion of the surface of the wall to be cooled to form a heat transfer path between the surface of the wall and the cooling fluid; andfastening the cooling panel to the surface of the wall in a manner that enables the cooling panel to be replaced without materially affecting or requiring disassembly of the wall or requiring the dismantling of any other cooling panel affixed to the outer surface of the wall. The method of claim 11 wherein a length of the cooling flow channel is a relatively small increment of the length of the transition. The method of claim 11 wherein the cooling panel defines a plurality of distinct parallel cooling flow channels. The method of claim 13 wherein adjacent parallel cooling flow channels direct the cooling fluid in opposite directions. The method of claim 11 including the step of attaching a plurality of cooling panels to the turbine transition member. The method of claim 15 including the step of removing one cooling panel from the surface of the liner and replacing the one cooling panel with a second cooling panel.