公开(公告)号：US12253050B2

公开(公告)日：2025-03-18

申请号：US17658903

申请日：2022-04-12

Applicant: General Electric Company

Inventor： Arin Elspeth Lastufka Cross ,  Krishnakumar Venkatesan

IPC: F02K7/16 ,  F02C6/00 ,  F02C6/08 ,  F02C7/042 ,  F02C7/057 ,  F02C7/18 ,  F02K1/06 ,  F02K7/14 ,  F02K7/20 ,  F23R7/00

Abstract: A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.

公开(公告)号：US11619172B1

公开(公告)日：2023-04-04

申请号：US17683445

申请日：2022-03-01

Applicant: General Electric Company

Inventor： Hannah Erin Bower ,  Daniel Louis Depperschmidt ,  Kapil Kumar Singh ,  Sarah Marie Monahan ,  Arin Elspeth Lastufka Cross

IPC: F23R3/00 ,  F02C7/264

Abstract: A detonation combustion system includes a detonation combustor. The detonation combustor includes a detonation manifold and one or more detonation chamber walls defining a detonation chamber. The detonation manifold includes a plurality of detonation fluid pathways defined by a monolithic structure of the detonation manifold, and a plurality of detonation orifice groups respectively including a plurality of detonation orifices disposed about a surface of the detonation manifold. Respective ones of the plurality of detonation orifice groups provide fluid communication from a corresponding one of the plurality of detonation fluid pathways to the detonation chamber through the plurality of detonation orifices corresponding to the respective one of the plurality of detonation orifice groups. The plurality of detonation orifices may be symmetrically oriented about a reference element of the detonation combustor.

公开(公告)号：US20250116244A1

公开(公告)日：2025-04-10

申请号：US18377151

申请日：2023-10-05

Applicant: General Electric Company

Inventor： Kapil Singh ,  Daniel Depperschmidt ,  Arin Elspeth Lastufka Cross ,  Sarah M. Monahan

IPC: F02K9/66 ,  F02K9/52 ,  F02K9/60

Abstract: Combustor systems are provided that include rotating detonation combustors (RDCs) arranged in series. In some embodiments, a combustor system includes a volume that receives a core oxidizer-fuel mixture. The combustor system includes a first RDC having a first detonation chamber. The first detonation chamber receives a first pilot oxidizer-fuel mixture and is bounded by a first channel formed in a peripheral wall. The combustor system further includes at least one additional RDC having a second detonation chamber. The second detonation chamber receives a second pilot oxidizer-fuel mixture and is bounded by a second channel formed in the peripheral wall. The first pilot oxidizer-fuel mixture reacts in the first detonation chamber and the second pilot oxidizer-fuel mixture reacts in the second detonation chamber to generate rotating detonation combustion waves that are guided by the first channel and the second channel to support a reaction that consumes the core oxidizer-fuel mixture.

公开(公告)号：US20230323809A1

公开(公告)日：2023-10-12

申请号：US17658903

申请日：2022-04-12

Applicant: General Electric Company

Inventor： Arin Elspeth Lastufka Cross ,  Krishnakumar Venkatesan

IPC: F02C6/00 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  F02C7/057

CPC classification number: F02C6/00 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  F02C7/057 ,  B64D2033/026 ,  F05D2220/323 ,  F05D2240/35

Abstract: A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.

公开(公告)号：US20230280035A1

公开(公告)日：2023-09-07

申请号：US17687873

申请日：2022-03-07

Applicant: General Electric Company

Inventor： Daniel Louis Depperschmidt ,  Kapil Kumar Singh ,  Aaron J. Glaser ,  Arin Elspeth Lastufka Cross ,  Sarah Marie Monahan ,  Hannah Erin Bower

IPC: F23R3/16 ,  F23R7/00 ,  F23R3/52 ,  F23R3/42

CPC classification number: F23R3/16 ,  F23R7/00 ,  F23R3/52 ,  F23R3/425 ,  F23R2900/03341

Abstract: A combustion system may include a detonation combustor comprising one or more detonation chamber walls defining a detonation chamber, a deflagration combustor comprising one or more deflagration chamber walls defining a deflagration chamber, and one or more conjugate chamber walls defining a conjugate chamber, with the conjugate chamber in fluid communication with the detonation chamber and the deflagration chamber. The detonation chamber includes a detonation region and a nozzle region, with the nozzle region providing fluid communication between the detonation region and the conjugate chamber.