公开(公告)号：US12078426B2

公开(公告)日：2024-09-03

申请号：US18190310

申请日：2023-03-27

Applicant: General Electric Company

Inventor： Ramon Martinez ,  Nicolas Kristopher Sabo ,  Curt Edward Hogan ,  Michael Stephen Popp ,  Jeffrey Douglas Rambo ,  Jared Matthew Wolfe

IPC: F28D7/00 ,  F28F7/02 ,  F28F9/02 ,  F28F13/12 ,  F28D21/00

CPC classification number: F28D7/0033 ,  F28F7/02 ,  F28F9/0265 ,  F28F9/0268 ,  F28F13/12 ,  F28D2021/0026 ,  F28F2009/0287 ,  F28F2255/18

Abstract: A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

公开(公告)号：US20240287934A1

公开(公告)日：2024-08-29

申请号：US18659339

申请日：2024-05-09

Applicant: General Electric Company

Inventor： Matthew Ryan Johns ,  Alex William Ariapad ,  Nicolas Kristopher Sabo ,  Jeffrey Douglas Rambo ,  Ramon Martinez ,  Jared Wolfe

IPC: F02C7/14

CPC classification number: F02C7/14 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/606

Abstract: A heat exchanger for an aircraft includes an inlet plenum housing defining an inlet plenum configured to receive a fluid and an outlet plenum housing defining an outlet plenum configured to discharge the fluid. Furthermore, the heat exchanger includes a core configured to heat or cool a first portion of the fluid, with the core defining a plurality of fluid passages extending from the inlet plenum to the outlet plenum. Moreover, the heat exchanger includes a passive bypass defining a passive bypass flow path fluidly coupled to and extending between the inlet plenum and the outlet plenum. As such, the passive bypass flow path is in parallel with at least a portion of the core such that a second portion of the fluid bypasses at least a portion of the core and flows continuously and unobstructed through the passive bypass flow path to the outlet plenum.

公开(公告)号：US20240183312A1

公开(公告)日：2024-06-06

申请号：US18439834

申请日：2024-02-13

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo

IPC: F02C7/18 ,  F02C3/22 ,  F02C6/08

CPC classification number: F02C7/185 ,  F02C6/08 ,  F02C3/22

Abstract: An aircraft propulsion system in includes a compressor section, a heat addition system, and an expansion section in serial flow arrangement, wherein the heat addition system is configured to receive a flow of gaseous fuel from a fuel system, and wherein the flow of gaseous fuel is provided to the heat addition system to generate combustion gases. A lubricant system is configured to provide a flow of lubricant through the propulsion system. A hydraulic system is configured to provide a flow of hydraulic fluid to an actuator at the propulsion system. A thermal management system is configured to provide a flow of fluid in thermal communication with the lubricant system and the hydraulic system. The thermal management system comprises a turbine configured to receive the flow of fluid via a fluid circuit extended in fluid communication from the compressor section.

公开(公告)号：US11976562B2

公开(公告)日：2024-05-07

申请号：US18297835

申请日：2023-04-10

Applicant: General Electric Company

Inventor： Steven Douglas Johnson ,  Julius John Montgomery ,  Brandon Wayne Miller ,  Robert Proctor ,  Bradley W. Fintel ,  Jeffrey Douglas Rambo

IPC: F01D11/24 ,  F01D5/03 ,  F01D11/18 ,  F02C6/08 ,  F02C7/18 ,  F01D25/12 ,  F01D25/14

CPC classification number: F01D11/24 ,  F01D5/03 ,  F01D11/18 ,  F02C6/08 ,  F02C7/185 ,  F01D25/12 ,  F01D25/14 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/30

Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

公开(公告)号：US11946415B2

公开(公告)日：2024-04-02

申请号：US17470032

申请日：2021-09-09

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo ,  Brandon Wayne Miller ,  William Joseph Bowden ,  Matthew Thomas Beyer ,  Michael John Simonetti

IPC: F02C7/10

CPC classification number: F02C7/10 ,  F05D2220/32 ,  F05D2260/213

Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

公开(公告)号：US11927134B1

公开(公告)日：2024-03-12

申请号：US18160375

申请日：2023-01-27

Applicant: General Electric Company

Inventor： Scott Alan Schimmels ,  Jeffrey Douglas Rambo ,  Timothy Richard DePuy ,  Steven B. Morris

IPC: F02C7/12 ,  F01D25/12 ,  F01D25/14

CPC classification number: F02C7/12 ,  F01D25/12 ,  F01D25/14 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2260/213

Abstract: A gas turbine engine is provided, having a turbomachine and a rotor assembly driven by the turbomachine and operable at a first blade passing frequency (f1) greater than or equal to 2,500 hertz and less than or equal to 5,000 hertz during a high power operating condition; a heat exchanger positioned within an annular duct and extending substantially continuously along the circumferential direction, wherein an effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for a high power operating condition, and wherein the heat exchanger comprises a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:




sin
⁢



⁢


(



2
×
π
×

f
1



a
1


×

L
i


)

2







wherein a1 is equal to 13,200 inches per second during the high power operating condition.

公开(公告)号：US11879392B2

公开(公告)日：2024-01-23

申请号：US18148518

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo

IPC: F02C7/22

CPC classification number: F02C7/22 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/213

Abstract: A gas supply system is provided herein. The gas supply system includes a fuel oxygen reduction unit having a circuit defining a gas flowpath for a flow of a stripping gas. A reservoir is in selective fluid communication with the fuel oxygen reduction unit and is configured to store a portion of the stripping gas from the circuit. The reservoir is further configured to be in selective fluid communication with the fuel system component when installed in a vehicle to provide the stored portion of the stripping gas to the fuel system component in response to detection of a purge condition.

公开(公告)号：US11761344B1

公开(公告)日：2023-09-19

申请号：US17724074

申请日：2022-04-19

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Brian Lewis Devendorf ,  Jeffrey Douglas Rambo ,  Brian Gene Brzek ,  Kevin Edward Hinderliter ,  Erich Alois Krammer ,  Arthur William Sibbach

IPC: F01D19/02 ,  F01D25/10 ,  F01D25/18

CPC classification number: F01D19/02 ,  F01D25/10 ,  F01D25/18 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/607 ,  F05D2260/85 ,  F05D2260/98

Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.

公开(公告)号：US11686537B2

公开(公告)日：2023-06-27

申请号：US17223284

申请日：2021-04-06

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo

IPC: B23K20/02 ,  B23P15/26 ,  F28F3/02 ,  B33Y80/00 ,  B23K20/00 ,  B33Y40/20 ,  B33Y10/00 ,  B23K101/14

CPC classification number: F28F3/025 ,  B23K20/002 ,  B23K20/02 ,  B23P15/26 ,  B33Y40/20 ,  B33Y80/00 ,  B23K2101/14 ,  B33Y10/00 ,  F28F2275/061

Abstract: A method of manufacturing a heat exchanger is provided. The method includes forming a first substrate by additively manufacturing a body defining a first outer surface and a second outer surface opposite the first outer surface, a first partial fluid flow channel formed within the first outer surface, a second partial fluid flow channel formed within the second outer surface, and at least one internal fluid flow channel completely formed within the body, and coupling the first substrate to a second substrate including a partial fluid flow channel formed within a surface of the second substrate such that the first partial fluid flow channel of the first substrate and the partial fluid flow channel of the second substrate combine to form a combined fluid flow channel.

公开(公告)号：US20230090415A1

公开(公告)日：2023-03-23

申请号：US17483229

申请日：2021-09-23

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Jeffrey Douglas Rambo ,  Daniel Alan Niergarth ,  Scott Alan Schimmels

IPC: F02C7/18 ,  F02C9/18

Abstract: A method of detecting an airflow fault condition in a gas turbine engine, the method including: operating the gas turbine engine with a thermal transport bus having an intermediary heat exchange fluid flowing therethrough; determining a performance characteristic of the intermediary heat exchange fluid in the thermal transport bus is outside of a predetermined range, wherein the performance characteristic includes a temperature, a pressure, a flowrate, or a combination thereof; and indicating an airflow fault condition in response to determining the performance characteristic is outside of the predetermined range.