Abstract: A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive. A method of cooling a propulsion system is also disclosed.

Abstract: A method for automatically generating an audio signal, the method comprising receiving a source audio signal analyzing the source audio signal to identify a musical parameter characteristic thereof obtaining a supplemental audio signal based on the identified musical parameter characteristic and combining the source audio signal and the supplemental audio signal to form an extended audio signal.

Abstract: A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive.

Abstract: A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive. A method of cooling a propulsion system is also disclosed.

Abstract: A method for automatically generating an audio signal, the method comprising receiving a source audio signal analyzing the source audio signal to identify a musical parameter characteristic thereof obtaining a supplemental audio signal based on the identified musical parameter characteristic and combining the source audio signal and the supplemental audio signal to form an extended audio signal.

Abstract: A vane assembly includes a rotatable airfoil that extends between a radially inner platform and a radially outer platform and has a leading edge and a trailing edge. A thrust projection is fixed relative to the rotatable airfoil. The thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second direction.

Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.

Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.

Abstract: A vane assembly includes a rotatable airfoil that extends between a radially inner platform and a radially outer platform and has a leading edge and a trailing edge. A thrust projection is fixed relative to the rotatable airfoil. The thrust projection includes a first thrust surface for supporting radial loads in a first radial direction and a second thrust surface for supporting radial loads in a second direction.

Abstract: A core compartment aft vent is disclosed. The core compartment aft vent may include a flexible core engine cowl surrounding a core engine case. A plurality of circumferentially spaced bumpers may be disposed within the aft vent and in operative contact with the flexible core engine cowl.

Abstract: An environmental control system is provided. The environmental control system may receive pressurized air from a single supply line. A pressure regulating turbomachine may be located within the supply line. A motor-generator may be coupled to the pressure regulating turbomachine. In response to a pressure in the supply line being less than a desired pressure in the environmental control system, the motor-generator may supply energy to the pressure regulating turbomachine, causing the pressure regulating turbomachine to function as a compressor. In response to a pressure in the supply line being greater than a desired pressure in the environmental control system, the pressure regulating turbomachine may function as a turbine and supply energy to the motor-generator.

Abstract: An environmental control power generation system is provided. The system may include a turbine and a generator. The system may be configured to provide air form a high pressure bleed port and/or a low pressure bleed port to the turbine. The turbine may be configured to reduce the pressure of the supplied air and generate power through the generator. The power may be supplied to an aircraft power distribution system.

Abstract: A compressor of a gas turbine engine includes a plurality of rotors rotatable about a central longitudinal axis, a plurality of stators, and a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators. The inner case wall includes a plurality of first slots located in a first section of the circumferential inner case wall and a plurality of second slots located in at least one second section of the circumferential inner case wall. A first area of each of the first slots is greater than a second area of each of the second slots. A circumferential manifold is located outwardly of the inner case wall including a port. At least one of the plurality of second slots is located proximate to the port.

Abstract: A cooling arrangement for a gas turbine engine according to an example of the present disclosure includes, among other things, an offtake duct that has an offtake inlet coupled to a cooling source, the offtake duct defining a throat, and a valve downstream of the throat. The valve couples the offtake duct and a first cooling flow path. The valve is operable to selectively modulate flow through the offtake duct. A bleed passage includes a bleed inlet coupling the offtake duct and a second cooling flow path. The bleed inlet is defined at a location between the offtake inlet and the throat, inclusive.

Abstract: A core compartment aft vent is disclosed. The core compartment aft vent may include a flexible core engine cowl surrounding a core engine case. A plurality of circumferentially spaced bumpers may be disposed within the aft vent and in operative contact with the flexible core engine cowl.

Abstract: A fluid pressure regulating system includes a turbomachine configured and adapted to pressurize fluid in a first mode and to depressurize fluid in a second mode. An energy exchange device is operatively connected to the turbomachine to provide power to drive the turbomachine in the first mode to pressurize fluid, and to be driven by the turbomachine in the second mode to receive power from depressurization of fluid. The turbomachine and energy exchange device are configured and adapted to selectively switch between the first and second modes to output fluid at a substantially constant pressure using fluid supplied at pressures that vary ranging from above and below the substantially constant pressure.

Abstract: An environmental control system is provided. The environmental control system may receive pressurized air from a single supply line. A pressure regulating turbomachine may be located within the supply line. A motor-generator may be coupled to the pressure regulating turbomachine. In response to a pressure in the supply line being less than a desired pressure in the environmental control system, the motor-generator may supply energy to the pressure regulating turbomachine, causing the pressure regulating turbomachine to function as a compressor. In response to a pressure in the supply line being greater than a desired pressure in the environmental control system, the pressure regulating turbomachine may function as a turbine and supply energy to the motor-generator.

Abstract: An environmental control power generation system is provided. The system may include a turbine and a generator. The system may be configured to provide air form a high pressure bleed port and/or a low pressure bleed port to the turbine. The turbine may be configured to reduce the pressure of the supplied air and generate power through the generator. The power may be supplied to an aircraft power distribution system.

Abstract: A compressor of a gas turbine engine includes a plurality of rotors rotatable about a central longitudinal axis, a plurality of stators, and a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators. The inner case wall includes a plurality of first slots located in a first section of the circumferential inner case wall and a plurality of second slots located in at least one second section of the circumferential inner case wall. A first area of each of the first slots is greater than a second area of each of the second slots. A circumferential manifold is located outwardly of the inner case wall including a port. At least one of the plurality of second slots is located proximate to the port.

Abstract: The claimed invention provides for new sample preparation methods enabling direct sequencing of PCR products using pyrophosphate sequencing techniques. The PCR products may be specific regions of a genome. The techniques provided in this disclosure allows for SNP (single nucleotide polymorphism) detection, classification, and assessment of individual allelic polymorphisms in one individual or a population of individuals. The results may be used for diagnostic and treatment of patients as well as assessment of viral and bacterial population identification.