Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.

Abstract: A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.

Abstract: A hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

Abstract: An exemplary cooling system includes a heat transfer device having a base and a plurality of curved fins defining a curved air flow channel. Air flow is provided through the air flow channel, and a plurality of openings through a fin communicate air flow from a first side to a second side of the curved fin.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream to enhance penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. Embodiments of the arrangement can comprise a collar around the openings, multiple openings that comprise a larger opening and a smaller opening positioned downstream, pairs of openings and associated collars symmetric relationship, and nozzles on the inner side of the wall.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

Abstract: A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption.

Abstract: An emission treatment system includes a first separation device that is operable to introduce one or more sorbents into an exhaust stream having emission products. The sorbent captures the emission products such that the exhaust stream includes sorbent with captured emission products. A second separation device located downstream from the first separation device receives the exhaust stream and utilizes an electrostatic potential to separate the sorbent with captured emission products from the exhaust stream into a discharge stream to produce a clean stream.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption.