General Electric Company

Ge Oil & Gas Esp, Inc.

Baker Hughes Esp, Inc.

Baker Hughes Oilfield Operations LLC

Adam Rasheed

Anthony John Dean

Venkat Eswarlu Tangirala

Narendra Digamber Joshi

Pierre Francois Pinard

Christian Lee Vandervort

James Fredric Wiedenhoefer

Christopher Donald Johnson

Brian Gene Brzek

David Toledano

David Michael Chapin

Justin Thomas Brumberg

Ross Hartley Kenyon

Mark Joseph Pombles

Aristotelis E Thanos

Ronald Scott Bunker

Thomas Michael Lavertu

Douglas Carl Hofer

Seyed Gholamali Saddoughi

Jeremy Daniel Van Dam

Ephraim J Gutmark

Abha Moitra

Dustin Wayne Davis

Matthew Patrick Boespflug

Shyam Sivaramakrishnan

Keith Robert McManus

Mohammed Mounir Shalaby

Bruce J Badding

Michael Colan Moscinski

Aaron J Glaser

Jinfeng Zhang

Edward Joseph Hall

Kevin Michael Hinckley

Ilkin Onur Dulgeroglu

Steven Jay Tyber

Nitish Umang

Aisha Yousuf

Fuhua Ma

Paul Whitson Dom, Jr

Peirre Francois Pinard

Jonathan Arnowitz

Victor Manuel Perez

Garry Marchment

Reejo Mathew

According to one embodiment, there is provided herein a system and method for producing a well lifecycle lift plan that includes considerations of multiple types of lift, multiple lift configurations associated with each lift type, and can be used to provide a prediction of when or if it would be desirable to change the lift plan at some time in the future. Another embodiment utilizes a heuristic database with rules that might be used to limit the solution space in some instances by restricting the solution to feasible configurations. A further embodiment teaches how multiple individual well optimization results might be combined with a reservoir model to obtain an optimized lift schedule for an entire field.

System and method for well artificial lift lifecycle planning

According to some embodiments, system and methods are provided, comprising an installed product, including a plurality of components; a computer programmed with a damage metric model for the installed product, the damage metric model for providing an estimate of an extent of damage on one or more components; the computer programmed with a dynamic process control model for providing a dynamic response of the installed product with respect to its one or more operating parameters; the computer further programmed with a true-up model for providing a control action to reduce an uncertainty of the estimate provided by the damage metric model; the computer including a processor and a memory in communication with the processor, the memory storing the damage metric model and the true-up model; the memory storing additional program instructions, the processor operative with the additional program instructions to perform functions as follows: receiving an estimate output of the damage metric model, wherein the output includes the estimate of the extent of damage on the one or more components; generating, via the dynamic process control model, an operating response of the installed product to the received estimate output; in response to receipt of the estimate output, executing the true-up model; and generating, via execution of the true-up model, the plan to reduce uncertainty of the estimate output. Numerous other aspects are provided.

Sensing and computing control system for shaping precise temporal physical states

System and method for well lifecycle planning visualization

A method of generating a recommendation of terms of an aircraft services contract is disclosed. Operations data pertaining to a planned usage of each aircraft of a fleet of aircraft is received. The operations data pertains to the fleet of aircraft for which an aircraft services customer seeks to enter into a services contract with an aircraft services provider. The operations data includes flight schedule data and flight policy data specific to each of the aircraft. Historical data pertaining to actual usage of other fleets of aircraft with respect to the flight schedule data and the flight policy data is analyzed. The analyzing includes generating an estimation of a risk associated with the services contract from the perspective of the aircraft services provider. An acceptable price for the services contract is generated such that the risk is mitigated from the perspective of the services provider. The terms pertaining to the service contract are communicated for presentation in a user interface. The terms include the acceptable price with respect to the operations data and the flight policy data.

Computing system to control the use of physical state attainment of assets to meet temporal performance criteria

A method of providing a first set of computer systems with access to a recommendation pertaining to operation of one or more assets based on the one or more assets being in revenue service or in repair is disclosed. Operations data and inspection data is collected at the first set of computer systems. The operations data and inspection data pertains to operating asset states of one or more fleets of aircraft over a time period. The operations data and the inspection data is stored in one or more databases of a second set of computer systems. Assumptions of control input values are derived for use by the first set of computer systems based on the operations data and the inspection data. A financial objective and constraints analysis is performed with a simulation system for one or more assets of the one or more fleets of aircraft. The cost savings analysis includes identifying a modification of at least one of a set of the control input values. An estimated reduction of forecast error related to operating and service costs is computed for the one or more assets over one or more time periods. The identifying is based on comparisons of a first subset of the operations data and the inspection data with a second subset of the operations data and the inspection data. The first set of computer systems is provided with access to the recommendation pertaining to operation of the one or more assets.

Constrained cash computing system to optimally schedule aircraft repair capacity with closed loop dynamic physical state and asset utilization attainment control

A hydrocarbon extractor (HE) evaluator system includes a central controller and an HE evaluator model that includes a hierarchical equipment model of heterogeneous HE type, subtype, and property, a plurality of rules arrangeable as a hierarchical equipment rule set, and as a hierarchical well feature rule set, a rules engine, the hierarchical well feature rule set formatted for a multi-factor comparison by the rules engine between heterogeneous HE types from disparate sources applied to the hierarchical equipment model. The rules engine configured to apply rules using class structure and one or more categories to an extracted portion of the hierarchical equipment model to generate results displayable to a user for determination of an HE type suitable for a particular well. A method for evaluating HE types and a non-transitory computer-readable medium containing instructions for a processor to perform the method are also disclosed.

System and method for evaluating heterogeneous hydrocarbon extractor systems for hydrocarbon wells

Display screen with graphical user interface of a layered data visualization element

A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.

Side-initiated augmentor for engine applications

The flow through the core of a hybrid pulse detonation combustion system is passed through a compressor and then separated into a primary flow, that passes directly to the combustor, and a bypass flow, which is routed to a portion of the system to be used to cool components of the system. The bypass flow is routed to a nozzle of the pulse detonation combustor. The flow is then passed back into the primary flow through the core downstream of where it was extracted.

Hot gas path component cooling for hybrid pulse detonation combustion systems

In one embodiment, a pulse detonation system includes a pulse detonation tube including a base tube and a thermally protective layer disposed adjacent to an inner surface of the base tube. The thermally protective layer is configured to limit temperature fluctuations at the inner surface of the base tube to less than approximately 20 degrees Celsius during operation of the pulse detonation system, and the thermally protective layer does not comprise a ceramic coating.

Pulse detonation system

A pulse detonation combustor including a plurality of nozzles engaged with one another via mating surfaces to support a gas discharge annulus in a circumferential direction. The pulse detonation combustor also including multiple pulse detonation tubes extending for the nozzles and a plurality of thermal expansion control joints coupled to the plurality of pulse detonation tubes. Each of the plurality of thermal expansion control joints is configured to facilitate independent thermal growth of each of the plurality of pulse detonation tubes. The thermal expansion control joints may be configured as a bellows expansion joint or a sliding expansion joint.

Pulse detonation combustor

A detonation chamber for a pulse detonation combustor including: a plurality of duplex tab obstacles disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of duplex tab obstacles enhance a turbulence of a fluid flow through the detonation chamber.

Duplex tab obstacles for enhancement of deflagration-to-detonation transition

A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.

System and method for passive valving for pulse detonation combustors

In one embodiment, a pulse detonation tube includes a continuous base tube having a substantially uniform wall thickness. The pulse detonation tube also includes a local flexural wave modifying feature configured to locally vary a flexural wave speed such that the flexural wave speed through the pulse detonation tube is different than an expected detonation wave speed, and/or to locally dissipate flexural wave energy.

Pulse detonation tube with local flexural wave modifying feature

A rotating valve assembly includes an inner cup having at least one inlet port; an outer cup having at least one inlet port, the outer cup rotatably mounted concentric with the inner cup by a bearing arrangement; and a cooling system located between the inner cup and the bearing arrangement for providing a thermal barrier between the inner cup and the bearing arrangement. The valve assembly also includes a labyrinth sealing arrangement located around the at least one inlet port of one of the inner and outer cups for preventing leakage of pressure waves generated by detonations or quasi-detonations within a combustion chamber of the inner cup.

Rotating valve assembly for high temperature and high pressure operation

Growing community of inventors

Glenville, NY, United States of America

Adam Rasheed