摘要:
Disclosed herein are apparatuses and systems for directing the flow of hot gas exiting a transition piece. In an embodiment, an aft frame an aft frame has an exit face that has an airfoil shape. In an embodiment, a transition piece aft exit has an airfoil shape.
摘要:
An impingement sleeve for a transition piece of a gas turbine is disclosed. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a joint defined between the first and second casings. The joint may include a plurality of fasteners configured to attach the first casing to the second casing.
摘要:
A system for supplying a working fluid to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for the working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube spirals between the flow sleeve and the liner.
摘要:
An apparatus is provided and includes a combustor, a transition piece and a flow conditioner. The combustor has a head end and defines a first flowpath along which a main flow is directable to flow in a downstream direction from the head end. The transition piece is disposable downstream from the combustor, has a forward end and defines a second flowpath along which the main flow is directable to flow in the downstream direction from the forward end. The flow conditioner includes an inner member coupled to the transition piece forward end, an outer member and aerodynamic elements supportively disposed between the inner and outer members to be interactive with a flow of fluid proceeding toward the combustor head end.
摘要:
A system for supplying a working fluid to a combustor includes a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides fluid communication for the working fluid to flow through the flow sleeve and into the combustion chamber, wherein the tube comprises an axial centerline. A first set of injectors are circumferentially arranged around the tube and angled radially with respect to the axial centerline of the tube, wherein the first set of injectors provide fluid communication for the working fluid to flow through a wall of the tube.
摘要:
A combustion system including a combustor; a combustor liner disposed within the combustor is provided. At least one primary fuel nozzle is provided to provide fuel to a primary combustion zone disposed proximate to the upstream end of the combustor liner. A transition duct is coupled to the downstream end of the combustor liner. A secondary nozzle assembly is disposed proximate to the downstream end of the combustor to provide fuel to a secondary combustion zone at locations predetermined to reduce peak thermal loads on the surface area of the transition duct.
摘要:
A system for supplying a working fluid to a combustor includes a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides fluid communication for the working fluid to flow through the flow sleeve and into the combustion chamber, wherein the tube comprises an axial centerline. A first set of injectors are circumferentially arranged around the tube and angled radially with respect to the axial centerline of the tube, wherein the first set of injectors provide fluid communication for the working fluid to flow through a wall of the tube.
摘要:
A system for supplying a working fluid to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for the working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube spirals between the flow sleeve and the liner.
摘要:
A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.
摘要:
A transition piece aft frame is provided and includes a manifold having an interior that is receptive of fuel and formed to define fuel injection holes configured to inject the received fuel from the manifold interior toward a main flow of products of combustion flowing through the manifold. The manifold includes a main body having an interior facing surface that faces the main flow of the products of the combustion and along which the fuel injection holes are defined.