Hanon Systems

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Siemens Aktiengesellschaft

Steven Koester

Ching-Pang Lee

Bradley Vernon Crenshaw

Jae Y Um

Mark Elliot Honkala

Brad Crenshaw

Harry Holloman

Kok-Mun Tham

Sin Chien Siw

Pete Edward Ganster

Anthony Waywood

Eric Chen

Rod Callahan

Kyung Jae Lee

Kanwal Bhatia

Jeong Ki Seo

Nan Jiang

Erik Johnson

Yuekun Zhou

Caleb Myers

Rance Stehouwer

Susana Isabel Nobre Salvador

Armando Nelson Pedro Da Silva

Adhlere Coffy

A fluid filter includes a body portion and a filter membrane portion. The body portion includes at least one aperture formed therein, wherein the filter membrane portion is disposed in the at least one aperture to filter contaminants from a fluid (e.g., a lubricant). The fluid filter is installed in a fluid passage of scroll compressor, wherein an axial movement of the fluid filter is restrained.

Fluid filter for a compressor

A compressor with a fluid separator is disclosed. The compressor is configured to compressor a first fluid (e.g., a refrigerant gas) having a second fluid (e.g., a lubricant) suspended therein. The fluid separator includes a main body having at least one aperture formed therethrough and is configured to separate the second fluid from the first fluid. The fluid separator is installed in a separation chamber of the compressor, wherein the fluid separator includes at least one retention feature to militate against axial movement of the fluid separator within the separation chamber.

Compressor with fluid separator

A passive discharge valve for a scroll compressor and method of use are disclosed. The passive discharge valve is configured to control a flow of fluid from a compression mechanism into a discharge chamber formed in a housing of the scroll compressor. The passive discharge valve comprises a main body including a common central aperture and one or more valvular conduits formed therein. The valvular conduits extend radially outwardly from the common central aperture and each has an inlet aperture in fluid communication with a discharge port of the compression mechanism and an outlet aperture in fluid communication with the discharge chamber. Each of the valvular conduits comprises a first flow path and a second flow path, wherein the second flow path intermittently intersects the first flow path to create a fluidic diode, which militates against reverse fluid flow (or backflow) during operation of the scroll compressor.

Multipath passive discharge valve for a compressor

An orbiting scroll of a scroll compressor includes a platter wall having a first face including a spiral structure projecting therefrom, a second face having a coupling structure configured to couple the orbiting scroll to a drive mechanism of the scroll compressor, and a circumferential surface connecting the first face to the second face in an axial direction of the platter wall. The orbiting scroll includes a mass reduction feature provided as an inwardly indented channel formed in the circumferential surface. The channel is further configured to form a retaining feature for retaining a rim of a mask during a process of coating the spiral structure of the first face with a surface coating.

Orbiting scroll platter mass reduction

A scroll compressor including a compression mechanism assembled with a valve assembly disposed in a housing. The compression mechanism including a fixed scroll and an orbit scroll. The fixed scroll includes a recessed pocket having a first indentation with a first injection port and a second indentation with a second injection port. A double reed structure of the valve assembly is disposed in the recessed pocket of the fixed scroll. The double reed structure includes a first reed configured to selectively permit a flow of a fluid through the first injection port and a second reed configured to selectively permit a flow of a fluid through the second injection port. The valve assembly further includes a valve member disposed adjacent the reed structure and a valve gasket disposed between the valve member and a portion of the housing.

Vapor injection structure for a compressor

A scroll compressor including a compression mechanism assembled with an injection valve assembly disposed in a housing. The compression mechanism including a fixed scroll and an orbit scroll. The fixed scroll includes a first borehole provided with a first injection port and a second borehole provided with a second injection port. The valve assembly includes a valve member, a double reed structure, a valve gasket, and a valve body. The double reed structure includes a first reed, an opposite second reed, and a connecting portion. The first reed is configured to selectively permit a flow of a fluid through the first injection port and the second reed configured to selectively permit a flow of a fluid through the second injection port.

Injection valve assembly for a compressor

A compressor operable in a heat pump mode of a refrigerant circuit includes a compression space in which a refrigerant is compressed. The compression space includes a discharge port and an injection port. A discharge chamber is fluidly coupled to the compression space by the discharge port. An injection chamber is fluidly coupled to the compression space by the injection port. A discharge recirculation pathway selectively provides fluid communication between the discharge chamber and the injection chamber. An injection of the recirculated refrigerant into the compression space through the injection port results in an increase in pressure, and hence temperature, of the refrigerant when discharged to the discharge chamber. The increased temperature of the discharged refrigerant increases a heating capacity of a condenser of the associated refrigerant circuit.

ETXV direct discharge injection compressor

A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

Turbine airfoil with trailing edge features and casting core

A valve assembly forms a check valve for a scroll compressor including a fixed scroll having a pair of injection ports fluidly coupled to a compression mechanism. The valve assembly includes a valve body having a pair of flow paths with each of the flow paths fluidly coupled to a corresponding one of the injection ports. An injection plate has a pair of injection holes. A reed structure is disposed between the injection plate and the valve body with the reed structure including a pair of reeds. Each of the reeds is configured to selectively provide fluid communication between a corresponding one of the injection holes and a corresponding one of the injection ports. A valve gasket is disposed between the reed structure and the valve body and includes a pair of flaps with each of the flaps configured to selectively contact a corresponding one of the reeds.

Vapor injection double reed valve plate

A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.

Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade

An integrated airfoil and platform cooling system () for a turbine rotor blade () includes an inlet () located at the root () for receiving a supply of a coolant (K), and at least one cooling leg () fluidly connected to the inlet () and configured for conducting the coolant (K) in a radially outboard direction. The cooling leg () is defined at least partially by a span-wise extending internal cavity () within a blade airfoil (). An entrance of the cooling leg () comprises a flow passage () that extends radially outboard and laterally into a blade platform (), so as to direct a radially outboard flowing coolant (K) to impinge on an inner side () of a radially outer surface () of the blade platform (), before leading the coolant (K) into the cooling leg ().

Turbine rotor blade with airfoil cooling integrated with impingement platform cooling

A turbine component including a shrouded airfoil with a flow conditioner configured to direct leakage flow and coolant to be aligned with main hot gas flow is provided. The flow conditioner is positioned on a shroud base radially adjacent to the tip of the airfoil and includes a ramped radially outer surface positioned further radially inward than a radially outer surface of the shroud base. The ramped radially outer surface extends from a first edge to a second edge in a direction generally from the suction side to the pressure side of the airfoil, such that the first edge is positioned further radially inward than the second edge. Multiple coolant ejection holes are positioned on the ramped radially outer surface. The coolant ejection holes are connected fluidically to an interior of the airfoil.

Shrouded turbine blade

A turbine blade including a pressure sidewall () and a suction sidewall (), and at least one partition rib () extends between the pressure and suction sidewalls () to define a serpentine cooling path () having adjacent cooling channels () extending in the spanwise direction (S) within the airfoil (). A flow turning guide structure () extends around an end of the at least one partition rib () and includes a first element () extending from the pressure sidewall () to a lateral location in the cooling path between the pressure and suction sidewalls (), a second element () extending from the suction sidewall () to the lateral location in the cooling path between the pressure and suction sidewalls (). The first and second elements () include respective distal edges () that laterally overlap each other at the lateral location.

Turbine blade with a non-constraint flow turning guide structure

An airfoil () is disclosed for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more converging-diverging exit slots () configured to increase the effectiveness of the cooling system () at the trailing edge () of the airfoil () by increasing the contact of cooling fluids with internal surfaces () of the pressure and suction sides () of the airfoil (). In at least one embodiment, the trailing edge cooling channel () may include one or more converging-diverging exit slots () to further pressurize the trailing edge cooling channel () and may be formed by a first and second ribs () extending between an outer walls () forming the pressure and suction sides (). The converging-diverging exit slot () may be formed from a first converging section () having an inlet () with a larger cross-sectional area than an outlet () and is formed from a second diverging section () having an inlet () with a smaller cross-sectional area than an outlet ().

Growing community of inventors

Toledo, OH, United States of America

Steven Koester