Abstract: A fan inlet case strut including a strut structural section; a strut cover disposed over a portion of the strut structural section; a strut airfoil section formed with a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge and extending from a first end to a second end, a camber line that extends between the leading edge and the trailing edge and a flow feature formed at a strut cover termination.

Abstract: Interference fits between CMC components and ancillary metal hardware within an engine casing can lead to damage to the CMC component and features thereof during assembly and/or over duration of many operating cycles. A method and arrangement are provided to prevent or ameliorate harmful effects resulting from interactions between CMC components and ancillary metal hardware by using spring elements. The spring elements are held in compression between an end wall of a bore hole in ancillary metal hardware and a structural feature, such as a flange, of the CMC component to urge the CMC component into a sealing and supporting engagement with a surface of ancillary metal hardware.

Abstract: An aircraft propulsion system includes a core engine and a bottoming cycle where a working fluid is circulated within a closed circuit. A first heat exchanger is used to transfer heat from a portion of thermal energy from the exhaust gas flow to working fluid of the bottoming cycle. A fuel/working fluid heat exchanger provides the cryogenic fuel to cool the working fluid exhausted from a bottoming turbine and before a bottoming compressor.

Abstract: A damage detection system includes one or more emitters, one or more receivers, and a controller. Emitters are arranged to transmit continuous beam or intermittent light pulses toward rotor blades during operation of a turbomachine. Light returns collected at the receivers define a light return amplitude profile. The controller analyzes the light return amplitude profile to identify light amplitude changes indicative of one or more damaged blades. When the light return profile satisfies one or more damage criteria, the controller outputs an indication of blade damage to another turbomachine controller, system, or display.

Abstract: An aircraft hybrid electrical propulsion (HEP) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an HEP controller in signal communication with the electrical system and the propulsion system. The HEP controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.

Abstract: A lubrication system including a bearing compartment housing defining a bearing compartment housing interior having a bearing compartment housing interior surface and a bearing compartment housing exterior having a bearing compartment housing exterior surface; a shaft supported by bearings located within the bearing compartment housing; and a lubricant trap formed on the bearing compartment housing interior surface, the lubricant trap configured to contain at least one lubricant, the at least one lubricant configured to be released onto the bearing.

Abstract: Examples described herein provide a method that includes providing a joint test action group interface of an engine control, the joint test action group interface being in a disabled state to prevent a device connected to the joint test action group interface from communicating with the engine control. The method further includes detecting whether a control access card is inserted into a port of the engine control. The method further includes, responsive to detecting that the control access card is inserted into the port of the engine control, performing an authentication using a credential stored on the control access card. The method further includes, responsive to successfully completing the authentication, enabling the joint test action group interface of the engine control to enable the device connected to the joint test action group interface to communicate with the engine control.

Abstract: A method for repairing a component of a gas turbine engine is provided. The method includes perforating apertures through a braze tape based on a shape of a degraded region of the component, and applying the braze tape to the component such that the braze tape covers the degraded region and the apertures surround a perimeter of the degraded region. The method also includes bonding the braze tape and the component via a thermal brazing treatment, and contouring the braze tape to conform to an original profile of the component based on monitoring depths of the apertures.

Abstract: A turbofan engine includes a propulsor section that has a propulsor shaft in driving engagement with a propulsor. An epicyclic gear system has a gear mesh lateral stiffness and a gear mesh transverse stiffness. A gear system input defines a gear system input lateral stiffness and a gear system input transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness. A first turbine section rotates at a first speed, and a second turbine rotates at a second speed that is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area of the first turbine, a second performance quantity is defined as the product of the second speed squared and the second area of the second turbine, and a performance quantity ratio is between 0.5 and 1.5.

Abstract: A method for producing a ceramic matrix composite component is disclosed. The method includes providing a plurality of first ceramic fiber plies including a plurality of interconnected tows and a plurality of first pores positioned between adjacent tows. The method includes applying a plurality of first ceramic particles within the plurality of first pores. Next, the method includes applying a plurality of second ceramic fiber plies onto an outer surface of the plurality of first ceramic fiber plies. The second ceramic fiber plies include a plurality of interconnected tows and a plurality of second pores positioned between adjacent tows. The method then includes applying a plurality of second ceramic particles within the plurality of second pores. Further, the plurality of second ceramic particles are larger than the plurality of first ceramic particles. Lastly, the method includes densifying the ceramic matrix composite preform to form the ceramic matrix composite component.

Abstract: An inspection system for a gas turbine engine includes a team of terrestrial drones each equipped with at least one inspection sensor and at least one processor. The processor is configured to choreograph operation of the terrestrial drones to each move along an associated drone-specific inspection path and collectively traverse an area of interest in a gas turbine engine; and operate the inspection sensor of each of the terrestrial drones to collect inspection data along the associated drone-specific inspection path.

Abstract: An assembly for an aircraft includes an airframe structure, a turbine engine and a heat exchanger. The turbine engine is mounted to the airframe structure. The heat exchanger is mounted to the airframe structure independent of the turbine engine. The heat exchanger extends axially along and circumferentially about the turbine engine.

Abstract: A system includes a laser drilling apparatus having a laser to drill into coating layers of a component. The component includes cooling holes through a substrate and an existing layer. The existing coating layer is stripped from the component. The locations of the cooling holes are mapped using a coordinate measurement machine that generates a macro file of the locations. The macro file is loaded onto the laser drilling apparatus. A new coating layer is applied that covers the cooling holes. The laser drilling apparatus collects data at the locations mapped to the macro file of the component having a new coating layer. A modification is made to the locations of the at least one cooling holes based on a parameter in the collected data. The laser drilling apparatus drills using the laser at the modified locations into the new coating layer.

Abstract: A turbine engine assembly includes a turbine section including at plurality of turbine stages through which the gas flow expands to generate a mechanical power output. An inter-turbine burner between at least two of the plurality of turbine stages reheats the gas flow. A condenser extracts water from the gas flow exhausted from the turbine section, and an evaporator heats the water extracted by the condenser to generate a steam flow with the steam flow communicated to the inter-turbine burner and added to the gas flow expanded through the turbine section.

Abstract: A gas turbine engine may include propulsor means for providing propulsion, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, and expansion means for driving the input of the reduction means. Static support means may support a bearing system that rotatably supports the expansion means and the propulsor means. The support means may support a forward engine mount at a first engine mount location axially near the reduction means relative to an engine axis when the engine is mounted. The support means may support an aft engine mount at a second engine mount location.

Abstract: A cover plate for enclosing a cooling cavity of a ceramic matrix composite (CMC) component of a turbine engine may include a base plate dimensioned to cover an open cooling cavity of the CMC component. The base plate has a first side facing the cooling cavity and at least one feature plate is attached to the first side of the base plate. At least one heat transfer augmentation feature is formed on the at least one feature plate and extends into the cooling cavity, wherein the at least one heat transfer augmentation feature is configured to cause turbulence in a cooling air flow within the cooling cavity. Thus, rather than forming complex heat transfer augmentation features on the cooling cavity of the CMC component itself, such features can be easily provided using metal plate or sheet material or separately-formed CMC elements on the cover plate.

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

Abstract: A method includes laying-up a fabric made of ceramic tows to form a fiber preform that has a repeating pattern of seal arc sections, densifying the fiber preform with a ceramic matrix material to form a densified ceramic matrix composite body, and then either before or after the densifying, cutting the fiber preform or the densified ceramic matrix composite body, respectively, along boundaries between the seal arc sections to separate the seal arc segments from each other.

Abstract: An assembly is provided for an aircraft powerplant. This assembly includes a vane structure, a first electric device and a cooling system. The first electric device is disposed within the vane structure. The first electric device includes a first device housing and first electrical circuitry. The first electrical circuitry is housed within an interior of the first device housing. The cooling system is configured to cool the first electrical circuitry. The cooling system includes a first heat exchanger and an air circuit. The first heat exchanger is disposed within the vane structure and thermally coupled to the first electric device. The air circuit extends within the vane structure from an airflow inlet into the air circuit, through the first heat exchanger, to an airflow outlet from the air circuit. The airflow inlet fluidly couples the air circuit to a volume external to the vane structure.

Abstract: A method and apparatus for applying a controlled thickness patch of repair material to a damaged surface adjacent a filleted surface disposed between a case surface and a strut is disclosed. A spacer is positioned on the case surface adjacent the filleted surface, with an outermost surface of the spacer dimensioned to intersect the filleted surface at a predetermined drop height from the case surface. Repair material is applied to the damaged surface by screeding with a straight edge. The straight edge is positioned with a first end against the outermost surface of the spacer and the filleted surface at the drop height, and a second end positioned against the strut or a guide mask disposed thereon so as to form a controlled thickness patch of repair material to the strut and filleted surface when the repair material is screeded.