United Technologies Corporation

Eaton Intelligent Power Limited

Keith A Santeler

Frank J Cunha

James Thompson Beals

Stephen Douglas Murray

Jacob A Snyder

John D Wiedemer

Brandon W Spangler

Bryan P Dube

Eric A Hudson

Christopher R Joe

Eric L Couch

Samuel D Draper

Michael K Turkington

Scott W Gayman

Jose A Lopes

Dilip M Shah

Daniel A Bales

Carl R Verner

Joel H Wagner

Shankar S Magge

Bret M Teller

Francisco J Cunha

Daniel A Snyder

Dinesh K Gupta

Sudhangshu Bose

Daniel F Paulonis

John J Marcin

Joshua E Persky

Glenn A Cotnoir

Stephen Showalter

Rolland Tracy James

Eric P Letizia

Venkat Seetharaman

Stephen D Murray

Jacob B Snyder

Christopher Joe

A separator assembly is provided for, among other things, separating debris particles from a fluid in a fluid system. In an embodiment, the separator assembly may include a housing forming an internal chamber. An inlet port may be in communication with the internal chamber of the housing, and the inlet port can be oriented in a tangential relationship relative to the internal chamber. A first debris separation ring may be disposed in the housing and can extend around an inner surface of the internal chamber. A second debris separation ring can be disposed in the housing and can extend around the inner surface of the internal chamber, wherein the second debris separation ring may be spaced from the first debris separation ring.

Multistage separator assembly

An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.

Centrifugal compressor with bleed flow splitter for a gas turbine engine

A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.

Filter system for blade outer air seal

A cooling microcircuit for use in a turbine engine component, such as a turbine blade, having an airfoil portion is provided. The cooling microcircuit has at least one inlet slot for introducing a flow of coolant into the cooling microcircuit, a plurality of fluid exit slots for distributing a film of the coolant over the airfoil portion, and structures for substantially preventing one jet of the coolant exiting through one of the fluid exit slots from overpowering a second jet of the coolant exiting through the one fluid exit slot.

Robust microcircuits for turbine airfoils

A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.

Refractory metal core coatings

At least one feedcore and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.

Investment casting pattern manufacture

A composite core for an investment casting process, the core including both a ceramic portion and a refractory metal portion, with the refractory metal portion being so disposed as to perform the function of a plurality of such refractory metal elements. In particular, a refractory metal element attached to a trailing edge of a ceramic element extends beyond the plane of a tip end of the ceramic element so as to replace the refractory metal element otherwise extending from the ceramic tip edge. The refractory metal element also extends beyond the space to be occupied by the wax casting, both in the direction of the tip end and the trailing edge such that improved placement and securing of the core is facilitated during the casting process. A further embodiment uses a single refractory metal element that extends into both the airfoil portion and an orthogonal extending platform portion thereof.

Composite core for use in precision investment casting

A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Investment casting core methods

At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.

An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.

Turbine airfoil platform cooling circuit

A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro-circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro-circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal convective efficiency, high film coverage, and high cooling effectiveness.

Micro-circuit platform

A turbine airfoil includes a plurality of cooling circuits embedded within the pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.

Microcircuit cooling for a turbine airfoil

A sacrificial core for forming an interior space of a part includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

Growing community of inventors

Middletown, CT, United States of America

Keith A Santeler