United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

Mastro, Jacob Peter

Stutz, Robert C.

Jacob Peter Mastro

Kyle L Forgette

Francis Parnin

Andrew V Schwendenmann

William G Sheridan

Michael E McCune

Reade W James

Martin J Walsh

Robert C Stutz

Daniel K DeVaux

Daniel K Devaux

A gas turbine engine includes, among other things, a bearing compartment, a shaft configured to rotate during operation of the gas turbine engine, and a sleeve configured to rotate with the shaft during operation of the gas turbine engine. The sleeve includes a variable radial dimension about a circumference of the sleeve. The engine further includes a seal statically mounted relative to the sleeve and configured to cooperate with the sleeve to seal the bearing compartment.

Rotating sleeve controlling clearance of seal assembly of gas turbine engine

An apparatus has: a first member (); a shaft () rotatable relative to the first member about an axis; and a seal system (). The seal system has a seal carrier () having: an axially-extending wall () having an inner diameter (ID) surface (); and a radially-extending wall () having a first surface (). A seal () is carried by the first member and has: an outer diameter (OD) surface (); and a seal face (). A seat () is carried by the shaft and has a seat face () in sliding sealing engagement with the seal face. One or more springs () bias the seal carrier relative to the first member so as to bias the seal face against the seat face. A key () spans an interface between the seal carrier and the seal.

Carbon face seal

An assembly for rotational equipment includes a scoop ring body and an insert. The scoop ring body is rotatable about a rotational axis. The scoop ring body extends radially between and inner radial side and an outer radial side. The scoop ring body includes a body material. The insert is mounted to the scoop ring body. The insert includes an insert material and a cutting edge. The insert material is different than the body material. The scoop ring body and the insert form a passage. The passage extends through the scoop ring body from an inlet at the outer radial side to an outlet at the inner radial side. The cutting edge is at the inlet. The passage extends within the scoop ring body between a first circumferential side and a second circumferential side. The passage at the first circumferential side is at least partially formed by the insert.

Scoop assembly for rotational equipment

An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has a seal carrier having: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. A seal is carried by the first member and has: an outer diameter (OD) surface; and a seal face. A seat is carried by the shaft and has a seat face in sliding sealing engagement with the seal face. One or more springs bias the seal carrier relative to the first member so as to bias the seal face against the seat face. At least one of the seal carrier inner diameter (ID) surface and seal outer diameter (OD) surface is formed by a coating.

A lubrication system may comprise a shaft including a shaft gear, a pump configured to supply a flow of lubricant to a component benefiting from lubrication and an input gear train coupled to the shaft gear and configured to drive the gear pump with a unidirectional rotation in response to a forward rotation and an reverse rotation of the shaft gear. The input gear grain may comprise a primary gear coupled to a common shaft. The input gear train may further comprise a forward shaft and a forward gear about the common shaft, wherein the forward gear is coupled to the forward shaft.

Dual direction windmill pump for geared turbofan engines

A method for controlling a gas turbine engine includes receiving, by a signal processor from a sensor, an operating condition of the gas turbine engine and determining, by the signal processor, whether the operating condition is within an acceptable threshold. In response to the operating condition being outside the acceptable threshold, the method includes restricting, by the signal processor, a subsequent engine restart of the gas turbine engine. Restricting the subsequent engine restart of the gas turbine engine may comprise preventing the subsequent restart. In various embodiments, restricting the subsequent engine restart of the gas turbine engine comprises limiting a subsequent operating state of the gas turbine engine after the subsequent restart.

Systems and methods for monitoring and controlling a gas turbine engine

A gas turbine engine includes a fan and a first drive shaft connected to the fan. A fan drive gear box connects the first drive shaft to a second drive shaft and is configured to allow the first drive shaft to rotate at a different speed than the second drive shaft. The gas turbine engine also includes a sprag clutch disposed circumferentially around the first shaft and connected to the first drive shaft. The sprag clutch is configured to allow rotation of the first drive shaft and the fan in a first direction while prohibiting rotation of the fan and the first drive shaft in a second direction.

Shaft anti-rotation device

According to one aspect of the present disclosure, a lubrication monitoring system is disclosed that includes a fan, a gear reduction operatively coupled to the fan, and a lubrication pump that is operatively coupled to the fan and is in fluid communication with the gear reduction. A first sensor is configured to detect a windmilling condition of the fan, and a second sensor is configured to detect an operational state of the lubrication pump. A controller in communication with the first and second sensors is configured to monitor the windmilling condition and the operational state of the lubrication pump, and command a status indicator in response thereto.

Method and apparatus for monitoring lubrication pump operation during windmilling

A lubrication system includes a shaft rotatable about an axis, a lubrication pump configured to supply a lubricant flow to a gear system, and a gear train coupled to the shaft and configured to drive the lubrication pump in a first direction responsive to rotation of the shaft in both the first direction and a second direction. A gas turbine engine and method are also disclosed.

Dual direction windmill pump for geared turbofan engine

What is described is a system for pumping lubricant to a component of a gas turbine engine. The system includes a fan gear coupled to a fan shaft of the gas turbine engine and configured to rotate in a forward direction and in a reverse direction based at least partially on a direction of wind relative to a fan of the gas turbine engine. The system also includes a first pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the forward direction. The system also includes a second pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the reverse direction.

Manhattan dual FDGS aux pump design

A disclosed lubrication system for turbofan engine includes a primary lubricant circuit, a primary pump driving lubricant through the primary circuit, an auxiliary lubricant circuit in communication with the primary lubricant circuit and an auxiliary lubricant pump driving lubricant through the auxiliary lubricant circuit. A first valve downstream of an outlet of auxiliary lubricant pump separates the auxiliary lubricant circuit from the primary lubricant circuit. A sensor is disposed within the auxiliary lubricant circuit for sensing pressure within the auxiliary lubricant circuit separate from a pressure within the primary lubricant circuit.

Fan drive gear system auxiliary pump monitoring system

A lubrication system for an engine including a scavenge pump configured to provide lubricant to the engine during a normal condition, an auxiliary pump configured to provide lubricant to the engine during an abnormal condition, a pressure sensor disposed at an outlet of the auxiliary pump for detecting a pressure created by the auxiliary pump, and a restriction device disposed in a conduit fluidly connecting the scavenge pump to the outlet of the auxiliary pump and configured to increase a first pressure produced by the auxiliary pump at the pressure sensor, wherein the first pressure is greater than a second pressure created by the scavenge pump at the pressure sensor.

FDGS auxiliary pump monitoring system

A lubrication system for a fan drive gear system includes a lubricant supply and a collection conduit for drawing lubricant from within the lubricant supply. The collection conduit includes a first opening and a second opening for withdrawing lubricant and supplying lubricant to a pump. During normal operation lubricant may be drawn through both first and second openings. During negative G operating conditions a fitting at the second opening blocks the second opening to prevent air from being drawn into the lubricant system and communicated to the pump.

Axial sealing gravity based siphon system

A debris discourager for a gas turbine engine is rotatable about an engine axis and extends between a fore end and an aft end. A portion of the debris discourager includes a non-uniform surface that generates a wind flow to prevent debris from entering a sealed interface.

Growing community of inventors

Glastonbury, CT, United States of America

Jacob Peter Mastro