Assembly for directing combustion gas
AssigneeSiemens Energy, Inc.
InventorsRichard C. Charron, David A. Little, Gary D. Snyder
Life of this patent
Estimating the term…
Loading patent…
AssigneeSiemens Energy, Inc.
InventorsRichard C. Charron, David A. Little, Gary D. Snyder
Estimating the term…
An arrangement is provided for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades including a first row of turbine blades. The arrangement includes a gas path cylinder, a cone and an integrated exit piece (IEP) for each combustor. Each IEP comprises an inlet chamber for receiving a gas flow from a respective combustor, and includes a connection segment. The IEPs are connected together to define an annular chamber extending circumferentially and concentric to an engine longitudinal axis, for delivering the gas flow to the first row of blades. A radiused joint extends radially inward from a radially outer side of the inlet chamber to an outer boundary of the annular chamber, and a flared fillet extends radially inward from a radially inner side of the inlet chamber to an inner boundary of the annular chamber.
An arrangement for delivering gases from a plurality of combustors of a can-annular gas turbine combustion engine to a first row of turbine blades, the arrangement comprising a gas path cylinder, a cone, and an integrated exit piece (IEP) for each combustor, wherein each IEP comprises a straight path portion for receiving a gas flow from a respective combustor via the cylinder and cone, and the IEP further includes a connection segment, wherein each IEP connects to an adjacent IEP at the connection segment of the adjacent IEP, and the connected IEPs define an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis, for delivering the gas flow to the first row of blades;
An arrangement for conveying combustion gas from a plurality of can-annular combustors of a gas turbine combustion engine to a first row of turbine blades, the arrangement comprising:
Dependencies are inferred from the claim text.