One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.

A blade for a turbomachine includes an airfoil portion and a root portion, the airfoil portion has an outer wall having a pressure side, suction side, leading edge and trailing edge, the outer wall extending between the leading edge and a trailing edge of the airfoil portion, a first cavity between the pressure side of the outer wall and a first inner wall, a second cavity between the suction side of the outer wall and a second inner wall. The first and second inner wall form a receiving cavity therebetween. The receiving cavity is fluidly connected to both the first and second cavity. The cooling fluid in the first and second cavity is conducted in a direction from the trailing edge to the leading edge and the cooling fluid in the receiving cavity is conducted in a direction from the leading edge to the trailing edge.

A component including a porous portion which may be permeable or impermeable to air, and a method for making. In one example, the component is a cooled wall segment for a gas turbine engine, including a body defining a contact surface configured to be in contact with circulating hot gas and an outer surface configured to be in contact with cooling air. The body includes a first portion with at least one retention element, and a porous second portion made of a porous material permeable to air, containing a plurality of interconnected pores, and having a porosity greater than that of the first portion. The second portion is engaged to the first portion, defines at least part of the contact surface, and defines at least part of a fluid communication between the outer surface and the contact surface through the interconnected pores. The wall segment may be for example a heat shield or shroud segment. Methods of forming components are also discussed.

An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a porous section having a porosity permitting a volume of fluid, such as air, to pass through the porous section.

An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

An apparatus and method for cooling an engine component, including an outer wall separating a hot fluid flow from a cooling fluid flow, using the cooling fluid flow to cool the engine component. A region in the component can include a plurality of film holes with a porous material to meter the flow of cooling fluid provided from the engine component.

Gas path components of gas turbine engines and methods for cooling the same using porous medium cooling systems are provided. The gas path component comprises a wall at least partially defining a cooling plenum and a porous medium cooling system. The wall includes a wall surface comprising a gas path surface and an opposing wall surface proximate the cooling plenum. The porous medium cooling system is disposed between the cooling plenum and the opposing wall surface. The porous medium cooling system comprises a perforated baffle and a porous material layer disposed between and adjacent the perforated baffle and the opposing wall surface. The wall includes a plurality of openings in fluid communication with the cooling plenum via the porous medium cooling system.

A turbine airfoil has a suction side wall and a pressure side wall of an airfoil cavity, through which a cooling fluid flows for cooling of the side walls. The suction side wall has one or more protrusions extending therefrom into the airfoil cavity. The protrusions are arranged such that: a number of the one or more protrusions on the suction side wall is higher than a number of protrusions on the pressure side wall; and/or a protrusion density on the suction side wall is higher than a protrusion density on the pressure side wall, and/or a total protrusion surface area on the suction side wall is larger than a total protrusion surface area on the pressure side wall, so that the heat transfer from the suction side wall to the cooling fluid is higher compared to that of the pressure side wall during operation of the turbomachine.

A gas turbine engine component is provided that can be cooled with a cooling media such as air using a variety of passages. In one form, cooling fluid is routed through a hole that exits at least partially through a pedestal formed between walls. A plurality of cooling holes can be provided through a trench face and in some forms can include a diffusion through a divergence in the hole exit. J-Hook passages can be provided through a trench face, and, in some forms, multiple trenches can be provided. A cooling hole having a neck portion can be provided, as can a cooling hole with one or more turns to reduce a total pressure. In one form, a corrugated cooling passage can be provided.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO.sub.2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO.sub.2 circulating fluid. Fuel derived CO.sub.2 can be captured and delivered at pipeline pressure. Other impurities can be captured.