Abstract: A bleed air valve comprises a piston that moves along a guide, where the piston includes a first surface and an opposing second surface. A pressure divider network includes a divider network inlet having an inlet cross sectional area in fluid communication with a fluid passage, a divider network outlet having an outlet cross sectional area in fluid communication with ambient pressure, and a network chamber in fluid communication with the divider network inlet and the divider network outlet. The network chamber has a pressure value between pressure at the divider network inlet and pressure at the divider network outlet. A shuttle valve includes a shuttle inlet and a shuttle outlet, where the shuttle outlet is in fluid communication with the first surface. An electromechanical valve receives a command signal and in response provides compressed air to an electromechanical valve output that is in fluid communication with the shuttle inlet.

Abstract: An anti-icing system of a nacelle inlet of an engine of an aircraft includes first and second direct acting valves and first and second control valve assemblies fluidly connected to the nacelle inlet. The first direct acting valve includes a first inlet, outlet, valve chamber, and piston. The first piston is positioned in the first direct acting valve. The first control valve assembly is fluidly connected to the first valve. The second direct acting valve includes a second inlet, outlet, valve chamber, and piston. The second piston is positioned in the second direct acting valve. The second direct acting valve is fluidly connected to the first direct acting valve in a series configuration. The second control valve assembly is fluidly connected to the second valve chamber.

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first end and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprising: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the pistons are configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between the first and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between first end and center portion, the first piston configured to block airflow through the fluid passage when in a closed position and allow airflow through the fluid passage when in an open position; a second piston located within the housing between second end and center portion, the second piston configured to block airflow through the fluid passage when in a closed position and allow airflow through the fluid passage when in an open position; and a manual override system configured to move from closed to open position at least one of the first and second pistons.

Abstract: An anti-icing system of a nacelle inlet of an engine of an aircraft includes first and second direct acting valves and first and second control valve assemblies fluidly connected to the nacelle inlet. The first direct acting valve includes a first inlet, outlet, valve chamber, and piston. The first piston is positioned in the first direct acting valve. The first control valve assembly is fluidly connected to the first valve. The second direct acting valve includes a second inlet, outlet, valve chamber, and piston. The second piston is positioned in the second direct acting valve. The second direct acting valve is fluidly connected to the first direct acting valve in a series configuration. The second control valve assembly is fluidly connected to the second valve chamber.

Abstract: An anti-icing system for an aircraft structure includes a cavity that has an exterior surface subject to ice accretion and a bleed source that is configured to provide a fluid to the cavity via a duct. The system includes multiple temperature sensors, disposed at the aircraft structure, with each temperature sensor configured to detect a temperature associated with an aircraft structure location. A controller is in communication with the temperature sensors. The controller is programmed to compare outputs of the temperature sensors and to determine a temperature sensor fault condition.

Abstract: A valve includes an inlet, an outlet, and a biasing element. The biasing element includes a first spring element, a second spring element, and a valve element. The second spring element includes at least one bimetallic disk including a first and second material. The first material includes a first coefficient of linear thermal expansion, and the second material includes a second coefficient of linear thermal expansion different than the first coefficient of linear thermal expansion. The valve element disposed on an end of the first spring element.

Abstract: A bearing spring support/damping apparatus has: a first end portion; a second end portion; and a flexible portion between the first end portion and the second end portion, and further comprising: a single outer diameter groove in the second end portion.

Abstract: A bearing spring support/damping apparatus has: a first end portion; a second end portion; and a flexible portion between the first end portion and the second end portion, and further comprising: a single outer diameter groove in the second end portion.

Abstract: A bearing damper assembly for a bearing compartment of a gas turbine engine includes a squirrel cage, a bearing support, an outer sleeve, and an inner sleeve. The bearing support is disposed radially outward from a portion of the squirrel cage. The outer sleeve extends axially from the bearing support. The inner sleeve is attached to the squirrel cage and is disposed radially inward from the outer sleeve. An outward surface of the inner sleeve has a first contoured portion having a first axially extending contour and an inner surface of the outer sleeve has a second contoured portion having a second axially extending contour. The outward surface of the inner sleeve and the inner surface of the outer sleeve define a gap extending between the first contoured portion and the second contoured portion. The gap forms a fluid damper.

Abstract: A bearing damper assembly for a bearing compartment of a gas turbine engine includes a squirrel cage, a bearing support, an outer sleeve, and an inner sleeve. The bearing support is disposed radially outward from a portion of the squirrel cage. The outer sleeve extends axially from the bearing support. The inner sleeve is attached to the squirrel cage and is disposed radially inward from the outer sleeve. An outward surface of the inner sleeve has a first contoured portion having a first axially extending contour and an inner surface of the outer sleeve has a second contoured portion having a second axially extending contour. The outward surface of the inner sleeve and the inner surface of the outer sleeve define a gap extending between the first contoured portion and the second contoured portion. The gap forms a fluid damper.

Abstract: A gas turbine engine is provided having a nacelle and a compressor section constructed and arranged to generate hot air. An anti-icing system is constructed and arranged to discharge the hot air from the compressor section to the nacelle. An anti-icing valve is positioned in the anti-icing system and constructed and arranged to control a flow of the hot air from the compressor section to the nacelle. The anti-icing valve includes a partially open position to constrict a flow of the hot air from the compressor section to the nacelle.

Abstract: A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

Abstract: According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.

Abstract: A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first end and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprising: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the pistons are configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between the first and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between first end and center portion, the first piston configured to block airflow through the fluid passage when in a closed position and allow airflow through the fluid passage when in an open position; a second piston located within the housing between second end and center portion, the second piston configured to block airflow through the fluid passage when in a closed position and allow airflow through the fluid passage when in an open position; and a manual override system configured to move from closed to open position at least one of the first and second pistons.

Abstract: An anti-ice system includes a duct that extends from a hot air bleed source to an anti-ice manifold and a direct-acting valve coupled to the duct. The duct may be configured to route hot air from the hot air bleed source to the anti-ice manifold at a regulated pressure and the direct-acting valve may include an inlet portion, a reference chamber, a force-type torque motor, an outlet portion, and a modulating sleeve. The inlet portion may be configured to be in hot air receiving communication with hot air from the hot air bleed source, the reference chamber may be configured to be in hot air receiving communication with the inlet portion, the force-type torque motor may be configured to control a reference pressure of hot air in the reference chamber, and the outlet portion may be configured in hot air receiving communication with the inlet portion via the modulating sleeve.

Abstract: Aspects of the disclosure are directed to a system comprising: a fastener that includes: a head that includes a feature pattern to accommodate installation and removal of the fastener, where the feature pattern is biased to provide a first torque capability in the installation of the fastener and a second torque capability in the removal of the fastener, and where the second torque capability is greater than the first torque capability.

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprises: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the first piston is configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.