977 results about "Suction stress" patented technology

A system for applying suction to a wound uses a reference airflow for monitoring system operation. A reference airflow (or “controlled leak”) to the suction source is provided when the system is in operation, such that deviation from the reference airflow can be monitored as an indication of a change in operation, such as a leak in the seal of the wound cover, a blockage of airflow from crimping of the suction conduit or overfill of the waste collector, or an inadvertent turn off or disconnect from the suction source.

A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors. The vane or blade design allows the turbine inlet temperature to increase over current technology levels while simultaneously reducing turbine cooling to low levels. A multi-wall cooling system is described, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade's pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to specific heat load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the suction surface is an independent rearward flowing serpentine). The cooling air for the independent circuits is supplied through separate passages at the base of the vane or blade. The cooling air follows intricate passages to feed the serpentine thin outer wall passages, which incorporate pin fins, turbulators, etc. These passages, while satisfying the aero/thermal/stress requirements, are of a manufacturing configuration that may be cast with single crystal materials using conventional casting techniques.

A rotor blade assembly and a method for reducing the noise of a rotor blade for a wind turbine are disclosed. The rotor blade has surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes a noise reducer configured on a surface of the rotor blade, the noise reducer including a plurality of noise reduction features. Each of the plurality of noise reduction features includes a first surface and a second surface. The first surface includes a first portion mounted to one of the pressure side or the suction side and a second portion configured to interact with wind flowing past the other of the pressure side or the suction side. The second surface interrupts an aerodynamic contour of the one of the pressure side or the suction side.

An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.

A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes a noise reducer configured on a surface of the rotor blade. The noise reducer includes a plurality of noise reduction features and a plurality of auxiliary noise reduction features. Each of the plurality of auxiliary noise reduction features is configured on one of the plurality of noise reduction features.

A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root, the rotor blade further defining a pitch axis. The rotor blade assembly further includes a noise reducer mounted to the rotor blade. The noise reducer includes a base plate defining a base line, a plurality of noise reduction features extending from the base line, and a plurality of apertures defined in the base plate. Each aperture is positioned on an opposite side of the base line from the plurality of noise reduction features such that the aperture is fully defined in the base plate.

A system operating in an environment having an ambient pressure, the system comprising: a reactor configured to combine a plasma stream, powder particles and conditioning fluid to alter the powder particles and form a mixture stream; a supply chamber coupled to the reactor; a suction generator configured to generate a suction force at the outlet of the reactor; a fluid supply module configured to supply the conditioning fluid at an original pressure; and a pressure regulation module configured to: receive the conditioning fluid from the fluid supply module, reduce the pressure of the conditioning fluid from the original pressure to a selected pressure relative to the ambient pressure regardless of any changes in the suction force at the outlet of the reactor, and supply the conditioning fluid at the selected pressure to the supply chamber.

A cooling system for a turbine airfoil of a turbine engine having a suction side near wall cooling chamber extending from the leading edge to the trailing edge. The suction side near wall cooling chamber may include a plurality of pin fins for increasing the cooling effectiveness of the suction side near wall cooling chamber. The pin fins may be formed in two or more regions having varying sizes and quantities per unit area to accommodate different cooling requirements across the airfoil. In one embodiment, cooling fluids may flow in a counterflow manner through the suction side near wall cooling chamber relative to a pressure side near wall cooling chamber. In another embodiment, the cooling fluids may flow from the leading edge through the suction side near wall cooling chamber and be exhausted through slots in the trailing edge.

A cooling system for a turbine blade of a turbine engine having a bifurcated mid-chord cooling chamber for reducing the temperature of the blade. The bifurcated mid-chord cooling chamber may be formed from a pressure side serpentine cooling channel and a suction side serpentine cooling channel. The pressure side and suction side serpentine cooling channels may flow counter to each other, thereby yielding a more uniform temperature distribution than conventional serpentine cooling channels.

Described herein are systems, apparatuses and methods for the design and use of a suction-controlled box for the measurement of stress-dependent soil and water characteristics, shear strength, volume changes and consolidation characteristics from a single unsaturated soil specimen. The suction-controlled box can include a suction control part and a mechanical loading part, which can apply various suctions and mechanical loadings to test a specimen for a full range of suctions. The suction-controlled box can also include a helical water compartment that can flush diffused air bubbles.

The present disclosure is directed to a modular rotor blade for a wind turbine and methods of assembling same. The rotor blade includes a blade root section, a blade tip section, at least one leading edge segment having a forward pressure side surface and a forward suction side surface, and at least one trailing edge segment having an aft pressure side surface and an aft suction side surface. Further, the leading edge segment and the trailing edge segment are arranged between the blade root section and the blade tip section in a generally span-wise direction. In addition, the leading edge segment and the trailing edge segment are joined at a pressure side seam and a suction side seam.

Airfoils are provided having non-monotonic meanline angle distributions and local negative camber along a length of the meanline between a point on a leading edge of the airfoil and a point on the trailing edge of the airfoil. The improved airfoil shape decreases the peak of a Mach number of a shock wave that develops in a passage between adjacent airfoils and attenuates or eliminates the shock wave at the suction surface of the airfoil within the passage. A blade constructed by this type of airfoil provides improved fluid flow in the passages between the airfoils, increased efficiency and an improved stall margin, among other benefits.

In a first intense suction, a supply line K is subjected to suction by a suction pump 23 with a portion of the supply line K held in a blocked state. Subsequently, the blocked portion of the supply line K is opened and trapped bubbles are discharged from a pressure chamber 46, which is located relatively upstream. In a subsequent second intense suction, the suction by the suction pump 23 is performed on the supply line K with a portion of the supply line K held in a blocked state, until a maximum negative pressure smaller than a maximum negative pressure of the first intense suction is obtained. The blocked portion of the supply line K is then opened, thus discharging trapped bubbles from an upper filter chamber 64, which is located relatively downstream.

A lifter device for separating the uppermost of a stack of flexible flat workpieces in suction holders for engaging a sheet when suction is applied thereto. At least one suction holder adjacent a side of the frame is movable independently of other suction holders spaced inwardly therefrom to bend an edge portion of the workpiece upwardly. A stop is provided on the frame to limit upward motion of the body of the sheet as the edge portion bends upwardly.

In a gas turbine bucket having a shank portion and an airfoil portion having leading and trailing edges and pressure and suction sides, an internal cooling circuit, the internal cooling circuit having a serpentine configuration including plural radial outflow passages and plural radial inflow passages, and wherein a coolant inlet passage communicates with a first of the radial outflow passages along the trailing edge, the first radial outflow passage having a plurality of radially extending and radially spaced elongated rib segments extending between and connecting the pressure and suction sides in a middle region of the first passage to prevent ballooning of the pressure and suction sides at the first radial outflow passage.