Abstract: Antimicrobial compositions including at least one acid and at least one anionic surfactant are provided. In particular, food contact antimicrobial compositions including at least one acid and at least one anionic surfactant provide a no-rinse compositions efficacious against Norovirus, having acceptable use solution pH that do not require use of personal protective equipment (PPE), are surface compatible and do not leave residues on treated surfaces are provided. Methods of cleaning a surface with the compositions are also provided.

Abstract: Antimicrobial compositions including at least one acid and at least one anionic surfactant are provided. In particular, food contact antimicrobial compositions including at least one acid and at least one anionic surfactant provide efficacious virucidal activity, including against Norovirus, having acceptable use solution pH that do not require use of personal protective equipment (PPE), are surface compatible and do not leave residues on treated surfaces. Methods of cleaning a surface with the compositions are also provided and may beneficially eliminate the need to rinse the antimicrobial compositions after use.

Abstract: A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils. The throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.

Abstract: A radially expandable backup ring (50) with relatively rigid segments (56) and relatively resilient segments (58) that are integral with one another to circumferentially urge the relatively rigid segments (56) together when the backup ring (50) expands. The backup ring (50) may radially expand to reduce or eliminate a radial gap between the backup ring (50) and a radially inwardly facing surface of a corresponding cased wellbore (22) to prevent or minimize axial extrusion of a corresponding sealing member (32), such as a compressible packer seal of a cased-hole retrievable packer assembly. The relatively resilient segments (58) allow the backup ring (50) to elastically expand and retract to prevent axial extrusion of the sealing member (32). The relatively rigid support segments (54) may be axially aligned with a corresponding relatively resilient segment (58) of the backup ring to prevent axial extrusion of the sealing member (32) through the corresponding relatively resilient segment (58).

Abstract: A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils. The throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.

Abstract: A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.

Abstract: A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils, and at 10% of the span of the adjacent ones of the airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value. The throat dimension at 5% of the span of the adjacent ones of the airfoils is less than 70% of the maximum value.

Abstract: A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.

Abstract: A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils, and at 10% of the span of the adjacent ones of the airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value. The throat dimension at 5% of the span of the adjacent ones of the airfoils is less than 70% of the maximum value.

Abstract: A radially expandable backup ring (50) with relatively rigid segments (56) and relatively resilient segments (58) that are integral with one another to circumferentially urge the relatively rigid segments (56) together when the backup ring (50) expands. The backup ring (50) may radially expand to reduce or eliminate a radial gap between the backup ring (50) and a radially inwardly facing surface of a corresponding cased wellbore (22) to prevent or minimize axial extrusion of a corresponding sealing member (32), such as a compressible packer seal of a cased-hole retrievable packer assembly. The relatively resilient segments (58) allow the backup ring (50) to elastically expand and retract to prevent axial extrusion of the sealing member (32). The relatively rigid support segments (54) may be axially aligned with a corresponding relatively resilient segment (58) of the backup ring to prevent axial extrusion of the sealing member (32) through the corresponding relatively resilient segment (58).

Abstract: Methods and apparatuses are provided for a compressor. The compressor includes a first stage having a first rotor and a first stator, and a second stage downstream from the first stage in a direction of a fluid flow. The compressor also includes a secondary flow system that directs fluid from the second stage into the first stator to improve at least one of a performance and a stability of the compressor.

Abstract: Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

Abstract: A device movable across a road to level emulsion thereon. A wheeled frame includes brushes extending downward to engage the emulsion. A manual worm gear connected between the frame and a towbar assembly positions the towbar mount to connect to a vehicle hitch and vertically moves the frame while maintaining the brush contacting plane. Spring biased guide wheels position the brushes to contact the road surface even though the surface is uneven.

Abstract: A device movable across a road to level emulsion thereon. A wheeled frame includes brushes extending downward to engage the emulsion. A manual worm gear connected between the frame and a towbar assembly positions the towbar mount to connect to a vehicle hitch and vertically moves the frame while maintaining the brush contacting plane. A linear actuator along with side plane adjusters position the brushes to contact the road surface even though the surface is uneven.

Abstract: Present embodiments include a sealing system configured to be disposed about a first wellhead component, wherein the sealing system includes a first seal and a pre-charging system configured to exert a first initial lateral loading force on the first seal to increase a first initial seal contact pressure of the first seal.

Abstract: Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

Abstract: Methods and apparatuses are provided for a compressor. The compressor includes a first stage having a first rotor and a first stator, and a second stage downstream from the first stage in a direction of a fluid flow. The compressor also includes a secondary flow system that directs fluid from the second stage into the first stator to improve at least one of a performance and a stability of the compressor.

Abstract: Present embodiments include a sealing system configured to be disposed about a first wellhead component, wherein the sealing system includes a first seal and a pre-charging system configured to exert a first initial lateral loading force on the first seal to increase a first initial seal contact pressure of the first seal.