Abstract: A gas turbine engine airfoil extending from an airfoil base to an airfoil tip at a free end of the airfoil and from a leading edge to a trailing edge of the airfoil has at least one recess extending into and circumferentially completely through the airfoil tip and located inwardly of the leading and trailing edges. The recess is located in an area of the airfoil tip subject to high tip vibratory stress and or rubs and may be a circular scallop having a scallop radius and a maximum depth of a few mills in a range of about 0.005-0.01 inches as measured from a nominal tip edge without the recess. The airfoil may be on a radial blade, a stator vane, or an impeller blade. An annular tip seal may surround a plurality of such airfoil tips with an airfoil tip clearance therebetween.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: An efficient configurable signal filter. The filter includes a first mechanism for receiving a first signal of a first type and a second signal of a second type. A second mechanism selectively filters the first signal during a first mode of operation, and filters the second signal during a second mode of operation. A third mechanism generates control signals. A fourth mechanism automatically configures the second mechanism to operate in the first mode of operation or the second mode of operation based on the control signals. In a specific embodiment, the first type of signal is characterized by a first rate, and the second type of signal is characterized by a second rate. The first signal and the second signal are digital ADC outputs. The second mechanism includes plural filter blocks, each having one or more Multiply-Accumulate (MAC) pipes. Each of the one or more MAC pipes include one or more MAC blocks that are each associated with a coefficient memory data structure of a coefficient memory.

Abstract: A digital signal-rate converting system. The system includes a first mechanism for receiving a digital input signal characterized by a first rate. A second mechanism interleaves the digital input signal in accordance with a predetermined pattern to yield an adjusted-rate digital signal. The adjusted-rate digital signal is representative of the digital input signal, such as a bandpass signal. In a more specific embodiment, the digital signal-rate converting system is an input interface of a rate-converting Digital-to-Analog Converter (DAC). The rate-converting DAC includes a DAC module, such as multi-bit or a 1-bit DAC module, for receiving the adjusted-rate digital signal and providing an analog output signal with a desired bandwidth or center frequency in response thereto. In the specific embodiment, the adjusted-rate digital signal approximates the digital input signal and is characterized by a rate based on a desired center frequency of the analog output signal.

Abstract: A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge, and forming a winglet that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, such that a radius extends between the winglet and at least one of the airfoil first side wall and the second side wall.

Abstract: A fan blade includes perforated anchor tangs, one with inboard corners and the remainder without. The corners are disposed in a complementary seat in a rotor disk for limiting blade pivoting during assembly.

Abstract: A fan outlet guide vane includes integral outer and inner platforms conforming to arcuate sides thereof, and multiple mounting bosses on the platforms. The platform sides are arcuate to conform with the vane sides for improving aerodynamic efficiency. The multiple mounting bosses improve mounting of the vanes to corresponding supporting rings.

Abstract: A fan blade includes an airfoil having a root and an integral platform. The platform includes forward and aft ends and arcuate first and second sides therebetween. The airfoil root is laterally offset closer to the platform first side than the second side. Impact loads with a trailing blade during a blade-out failure are accordingly distributed for reducing peak loading in the trailing blade and damage thereto.

Abstract: A system and method that provides for all-weather precision guidance of conventional air-to-surface weapons. The system and method employs a coherent monopulse radar disposed on a launch platform and a noncoherent passive (receive only) radar disposed on the weapon. The synthetic aperture radar generates a synthetic aperture radar monopulse map of an area around the target. The radar is used designate the location of the target, and transmit a sequence of alternating sum and simultaneous azimuth and elevation difference patterns centered on the target. The weapon includes a guidance system and seeker that is responsive to guidance commands transmitted by the synthetic aperture radar. The guidance system and seeker receives reflections of the alternating sum and combined azimuth and elevation difference pattern from the target, and the sum pulse is used by the weapon to acquire and track the azimuth and elevation difference pattern null on the target to fly an optimum trajectory to the target.