Abstract: A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

Abstract: A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: Disclosed herein are markers whose mutational status is associated with sensitivity to treatment with NAE inhibitors. Mutational status is determined by measurement of characteristics of markers associated with the marker genes. Compositions and methods are provided to assess markers of marker genes to predict response to NAE inhibition treatment.

Abstract: Disclosed herein are markers whose mutational status is associated with sensitivity to treatment with NAE inhibitors. Mutational status is determined by measurement of characteristics of markers associated with the marker genes. Compositions and methods are provided to assess markers of marker genes to predict response to NAE inhibition treatment.

Abstract: The present disclosure relates to methods for the treatment of cancer in patients in recognized need of such treatment. The methods comprise administering to such a patient an NAE inhibitor or a pharmaceutically acceptable salt thereof, such as ((1S,2S,4R)-4-(4-((1S)-2,3-dihydro-1H-inden-1-ylamino)-7H-pyrrolo[2,3-d]pyrimidin-7-yl)-2-hydroxycyclopentyl)methyl sulfamate (MLN4924) or {(1S,2S,4R)-4-[(6-{[(1R,2S)-5-chloro-2-methoxy-2,3-dihydro-1H-inden-1-yl]amino}pyrimidin-4-yl)oxy]-2-hydroxycyclopentyl}methyl sulfamate (I-216), and a hypomethylating agent or a pharmaceutically acceptable salt thereof, such as azacitidine or decitabine. Also disclosed are medicaments for use in the treatment of cancer.

Abstract: The invention provides isolated nucleic acids molecules, designated UBA3, UAE, or UBA6, or other E1 enzyme variant nucleic acid molecules, which encode novel E1 enzyme variant proteins. The invention also provides antisense nucleic acid molecules, recombinant expression vectors containing UBA3, UAE, or UBA6, or other E1 enzyme variant nucleic acid molecules, host cells into which the expression vectors have been introduced, and nonhuman transgenic animals in which a UBA3, UAE, or UBA6, or other E1 enzyme variant gene has been introduced or disrupted. The invention still further provides isolated UBA3, UAE, or UBA6, or other E1 enzyme variant proteins, fusion proteins, antigenic peptides and anti-UBA3, UAE, or UBA6, or other E1 enzyme variant antibodies. The invention provides methods to identify agents that inhibit UBA3, UAE, or UBA6, or other E1 enzyme variant expression or activity. Diagnostic and therapeutic methods utilizing compositions of the invention are also provided.

Abstract: A method for recovering oil from a subterranean, hydrocarbon-bearing formation includes at least one injection well and injecting a carrier fluid including a diverting agent into a high permeability pathway within the formation. An activating fluid is injected into the high permeability pathway within the formation, resulting in the precipitation or swelling of the diverting agent. The permeability of the high permeability pathway is decreased within the formation containing the diverting agent to a permeability less than the permeability of the adjacent areas of the formation. The carrier fluid may have a predetermined residence time within the formation prior to injecting an activating fluid; the step of injecting a carrier fluid comprising a diverting agent and injecting an activating fluid may be repeated. A mineralization fluid may be injected that is oversaturated or becomes oversaturated upon interacting with the acid gas that causes mineral precipitation to seal off high-permeability pathways.

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: A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.

Abstract: A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A method of machining a blade retention slot with an abrasive water jet machining. A straight blade retention slot along an X-axis then a at least one side of the straight blade retention slot is abrasive water jet machined to generate a curved side of the blade retention slot defined within an X-Y plane.

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 vane assembly has an outer support ring, an inner support ring, an outer liner ring, an inner liner ring, and a circumferential array of vanes. Each vane has a shell extending from an inboard end to an outboard end and at least partially through an associated aperture in the inner liner ring and an associated aperture in the outer liner ring. There is at least one of: an outer compliant member compliantly radially positioning the vane; and an inner compliant member compliantly radially positioning the vane.

Abstract: A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

Abstract: A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has an expansion ratio greater than or equal to about 5. The fan has a bypass ratio greater than or equal to about 8. In other features, a turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.