摘要:
One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
摘要:
One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
摘要:
A system for supplying pressurized fluid to a combustor of a gas turbine is disclosed. The system may include an end cover and a fuel nozzle extending from the end cover. The fuel nozzle may include a downstream end. Additionally, the system may include a cap assembly configured to receive at least a portion of the fuel nozzle. The cap assembly may include an upstream wall spaced apart from the downstream end, a downstream wall disposed proximate to the downstream end and a cap chamber defined between the upstream and downstream walls. Moreover, a conduit may extend through the end cover and the upstream wall such that a discharge end of the conduit is in flow communication with the cap chamber.
摘要:
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.
摘要:
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.
摘要:
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure extending between the combustion liner and the flow sleeve. The structure obstructs an airflow path through the air passage. The gas turbine combustor also includes an aerodynamic wake reducer configured to redirect an airflow around the structure to reduce a wake region downstream of the structure.
摘要:
The present application and the resulting patent provide a pre-nozzle mixing cap assembly positioned about a cap member of a combustor for mixing a flow of air and a flow of fuel. The pre-nozzle mixing cap assembly may include a fuel plenum in communication with the flow of fuel and a number of tubes in communication with the flow of air and extending through the fuel plenum. Each of the tubes may include a number of fuel holes therein such that the flow of fuel in the fuel plenum passes through the fuel holes and mixes with the flow of air.
摘要:
A system for supplying pressurized fluid to a combustor of a gas turbine is disclosed. The system may include an end cover and a fuel nozzle extending from the end cover. The fuel nozzle may include a downstream end. Additionally, the system may include a cap assembly configured to receive at least a portion of the fuel nozzle. The cap assembly may include an upstream wall spaced apart from the downstream end, a downstream wall disposed proximate to the downstream end and a cap chamber defined between the upstream and downstream walls. Moreover, a conduit may extend through the end cover and the upstream wall such that a discharge end of the conduit is in flow communication with the cap chamber.
摘要:
A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an airflow guide vane disposed in the air passage. The airflow guide vane includes an upstream vane portion and a downstream vane portion. The upstream vane portion is oriented at an angle from an axial axis of the gas turbine combustor. The downstream vane portion is aligned with the axial axis. The airflow guide vane is configured to remove a circumferential swirl of an airflow upstream of the airflow guide vane to straighten the airflow downstream of the airflow guide vane along the axial axis.
摘要:
Certain embodiments of the present disclosure include a combustor resonator having a non-uniform annulus between a combustor assembly and a resonator shell. The combustor resonator may further include resonator necks or passages having non-uniform lengths and geometries.