Mikro Systems, Inc.

Siemens Aktiengesellschaft

Raytheon Technologies Corporation

Siemens Energy, Inc.

Rtx Corporation

Benjamin E Heneveld

Ching-Pang Lee

Gary Brian Merrill

Allister William James

John R Paulus

Jill Klinger

Jon T Moore

John Joseph Marra

Michael P Appleby

Iain Fraser

Andrew Jeremiah Burns

Glenn E Brown

Kevin C Sheehan

Iain Alasdair Fraser

Iain A Fraser

A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.

Engine component

A method of forming an article including: contacting a fugitive tool with a powdered parent material; densifying the powdered material; and destructively removing the fugitive tool. A coating of a different material may be formed against the parent material using a similar approach.

Systems, devices and methods for spark plasma sintering

A blade body of a turbine blade, which defines an interior cavity fluidly communicative with coolant, is provided. The blade body includes an interior surface and one or more pins extending from the interior surface. The interior surface and the one or more pins are disposable to thermally interact with the coolant. At least one of the one or more pins includes a first section and a second section interposed between the first section and the interior surface. The first section has a larger cross-sectional area than the second section.

Ribbed pin fins

A gas turbine engine airfoil includes an outer wall including a suction side, a pressure side, a leading edge, and a trailing edge, the outer wall defining an interior chamber of the airfoil. The airfoil further includes cooling structure provided in the interior chamber. The cooling structure defines an interior cooling cavity and includes a plurality of cooling fluid outlet holes, at least one of which is in communication with a pressure side cooling circuit and at least one of which is in communication with a suction side cooling circuit. At least one of the pressure and suction side cooling circuits includes: a plurality of rows of airfoils, wherein radially adjacent airfoils within a row define segments of cooling channels. Outlets of the segments in one row align aerodynamically with inlets of segments in an adjacent downstream row such that the cooling channels have a serpentine shape.

Cooling configuration for a gas turbine engine airfoil

Certain exemplary embodiments can provide a system, machine, device, manufacture, and/or composition of matter configured for and/or resulting from, and/or a method for, activities that can comprise and/or relate to, investment casting a product in a mold, the product comprising at least one wall, the mold comprising a core, an inner primary shell, and an outer secondary shell.

Systems, devices, and methods involving precision component castings

A cooling channel (B) cools an exterior surface (or) or two opposed exterior surfaces (and). The channel has a near-wall inner surface () with a width (W1). Interior side surfaces () may converge to a reduced channel width (W2). The near-wall inner surface () may have fins () aligned with a coolant flow (). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel () may have two near-wall inner surfaces () parallel to two respective exterior surfaces (), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (A,B) increases cooling flow () into the corners (C) of the channel for more uniform and efficient cooling.

Component cooling channel

Certain exemplary embodiments can provide a system, machine, device, manufacture, circuit, and/or composition of matter adapted for and/or resulting from, and/or a method for activities that can comprise and/or relate to, a first form comprising: a plurality of surface artifacts that substantially spatially replicate a surface geometry of a stacked foil mold; and a prong that is adapted to form a hole in a cast product.

Systems, devices, and/or methods for producing holes

A gas turbine engine component, including: a pressure side () having an interior surface (); a suction side () having an interior surface (); a trailing edge portion (); and a plurality of suction side and pressure side impingement orifices () disposed in the trailing edge portion (). Each suction side impingement orifice is configured to direct an impingement jet () at an acute angle () onto a target area () that encompasses a tip () of a chevron () within a chevron arrangement () formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

A turbine blade () including an airfoil () having multiple interior wall portions () each separating at least one chamber from another one of multiple chambers (). In one embodiment a first wall portion (-) between first and second chambers () includes first and second pluralities of flow paths (P,S) extending through the first wall portion. The first wall portion includes a first region Rhaving a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening () in the first chamber (), through the first region and to an exit opening () in the second chamber () which path distance is greater than the first thickness.

Turbine blade incorporating trailing edge cooling design

A cooling arrangement () for a gas turbine engine component, the cooling arrangement () having a plurality of rows () of airfoils (), wherein adjacent airfoils () within a row () define segments () of cooling channels (), and wherein outlets () of the segments () in one row () align aerodynamically with inlets () of segments () in an adjacent row () to define continuous cooling channels () with non continuous walls (), each cooling channel () comprising a serpentine shape.

Cooling arrangement for a gas turbine component

A ceramic casting core, including: a plurality of rows () of gaps (), each gap () defining an airfoil shape; interstitial core material () that defines and separates adjacent gaps () in each row (); and connecting core material () that connects adjacent rows () of interstitial core material (). Ends of interstitial core material () in one row () align with ends of interstitial core material () in an adjacent row () to form a plurality of continuous and serpentine shaped structures each including interstitial core material () from at least two adjacent rows () and connecting core material ().

Growing community of inventors

Newmarket, NH, United States of America

Benjamin E Heneveld