Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.

Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.

Abstract: A gas turbine engine includes a first duct, a second duct, and a bladder. The bladder is disposed in the first duct and communicates with the second duct. A first gas flow is capable of passing through the first duct and a second gas flow is capable of passing through the second duct. The bladder is adapted to receive a bleed gas flow from the second duct and inflate within the first duct, thereby decreasing an area in the first duct through which the first gas flow is capable of traveling.

Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.

Abstract: A gas turbine engine includes a first duct, a second duct, and a bladder. The bladder is disposed in the first duct and communicates with the second duct. A first gas flow is capable of passing through the first duct and a second gas flow is capable of passing through the second duct. The bladder is adapted to receive a bleed gas flow from the second duct and inflate within the first duct, thereby decreasing an area in the first duct through which the first gas flow is capable of traveling.

Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.

Abstract: A cooling liner having a liner hot sheet formed as a relatively thick iso-grid structure having iso-grid ribs, which extend from a surface between the ribs. A multitude of metering sheets are mounted directly to the liner hot sheet surface. Each metering sheet is mounted to the iso-grid to define a multitude of discrete chambers. A seal is located in a pattern along a subset of the iso-grid ribs to further segregate the surface covered by each metering sheet into a further number of discrete subchambers. Each metering sheet includes a multitude of metering sheet apertures and the surface between the iso-grid ribs of the liner hot sheet include a multitude of hot sheet apertures. By varying the ratio between the number of metering sheet apertures and the number of hot sheet apertures, the pressure in each chamber is defined to efficiently maintain the minimum desired pressure ratio across the hot sheet without undue wastage of cooling airflow.

Abstract: A cooling liner having a liner hot sheet formed as a relatively thick iso-grid structure having iso-grid ribs, which extend from a surface between the ribs. A multitude of metering sheets are mounted directly to the liner hot sheet surface. Each metering sheet is mounted to the iso-grid to define a multitude of discrete chambers. A seal is located in a pattern along a subset of the iso-grid ribs to further segregate the surface covered by each metering sheet into a further number of discrete subchambers. Each metering sheet includes a multitude of metering sheet apertures and the surface between the iso-grid ribs of the liner hot sheet include a multitude of hot sheet apertures. By varying the ratio between the number of metering sheet apertures and the number of hot sheet apertures, the pressure in each chamber is defined to efficiently maintain the minimum desired pressure ratio across the hot sheet without undue wastage of cooling airflow.

Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

Abstract: A turbine engine has a centerbody within a gas flowpath and a downstream tailcone and a pilot at an upstream end of the tailcone. A flameholder is positioned in the flowpath outboard of the centerbody. The pilot has a first surface diverging in a downstream direction.

Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.

Abstract: A turbine engine has a centerbody within a gas flowpath and a downstream tailcone and a pilot at an upstream end of the tailcone. A flameholder is positioned in the flowpath outboard of the centerbody. The pilot has a first surface diverging in a downstream direction.