Abstract: An anti-icing system includes a nozzle assembly, a bleed air supply, a bleed control valve assembly, and a controller. The bleed air supply is configured to direct pressurized bleed air to the nozzle assembly. The bleed air supply includes a first pressure sensor configured to measure a first pressure of the pressurized bleed air. The bleed control valve assembly includes a control valve and a valve actuator. The control valve is positionable to control a flow rate of the pressurized bleed air. The valve actuator is configured to control a position of the control valve. The controller is configured to identify a power condition of the bleed air supply as a first power condition or a second power condition and control the valve actuator to position the control valve in a fully opened position for the first power condition and in a predetermined position based on the first pressure for the second power condition.

Abstract: An air inlet section for an enclosure for an aircraft engine is provided that includes an inner barrel panel, an outer barrel panel, a lipskin and a forward bulkhead. The lipskin extends between an inner barrel end and an outer barrel end. The inner barrel end is disposed proximate the forward end of the inner barrel panel and the outer barrel end is disposed proximate the forward end of the outer barrel panel. The forward bulkhead has a panel that extends between an outer radial end and an inner radial end. The inner barrel panel, the outer barrel panel, and the lipskin define an interior annular region, and the forward bulkhead defines a sub-portion of interior annular region. The outer radial end of the forward bulkhead panel is disposed forward of the inner radial end of the forward bulkhead panel.

Abstract: A bleed air system for a pneumatic system of an aircraft includes a low-pressure bleed tap configured to bleed a low-pressure compressed air from a low-pressure source; a high-pressure bleed tap configured to bleed a high-pressure compressed air from a high-pressure source; an upstream duct configured to receive one or both of the low-pressure compressed air and the high-pressure compressed air; a downstream duct configured to provide a regulated compressed air to the pneumatic system; a high-pressure shutoff valve positioned between the high-pressure bleed tap and the upstream duct; a low-pressure non-return valve positioned between the low-pressure bleed tap and the upstream duct; a pressure regulating and shutoff valve positioned between the upstream duct and the downstream duct, the pressure regulating and shutoff valve configured to generate the regulated compressed air; and a pressure relief valve positioned within the upstream duct.

Abstract: A control system for aircraft anti-icing is disclosed including a conduit coupled at a first end to a source of hot high-pressure bleed air, a control valve in fluid communication with the conduit and an injector head, wherein the control valve is in electronic communication with a controller and configured to regulate the flow of bleed air between the conduit and the injector head, and a first sensor in electronic communication with the controller and configured to report a first data. The system may initialize a control valve to an initial regulated pressure. The system may determine a control temperature and control the control valve based on the control temperature, the first data, and a set value.

Abstract: A control system for aircraft anti-icing is disclosed including a conduit coupled at a first end to a source of hot high-pressure bleed air, a control valve in fluid communication with the conduit and an injector head, wherein the control valve is in electronic communication with a controller and configured to regulate the flow of bleed air between the conduit and the injector head, and a first sensor in electronic communication with the controller and configured to report a first data. The system may initialize a control valve to an initial regulated pressure. The system may determine a control temperature and control the control valve based on the control temperature, the first data, and a set value.

Abstract: An air inlet section for an enclosure for an aircraft engine is provided that includes an inner barrel panel, an outer barrel panel, a lipskin and a forward bulkhead. The lipskin extends between an inner barrel end and an outer barrel end. The inner barrel end is disposed proximate the forward end of the inner barrel panel and the outer barrel end is disposed proximate the forward end of the outer barrel panel. The forward bulkhead has a panel that extends between an outer radial end and an inner radial end. The inner barrel panel, the outer barrel panel, and the lipskin define an interior annular region, and the forward bulkhead defines a sub-portion of interior annular region. The outer radial end of the forward bulkhead panel is disposed forward of the inner radial end of the forward bulkhead panel.