公开(公告)号：US10584878B2

公开(公告)日：2020-03-10

申请号：US15907854

申请日：2018-02-28

Applicant: Delavan Inc

Inventor： Brett A. Pfeffer ,  Jason A. Ryon

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/34 ,  F23D11/10 ,  F23D11/38 ,  F23D14/24 ,  B01F3/04 ,  B01F5/04 ,  F02C7/22 ,  B01F5/00

Abstract: A swirler includes a swirler body and a plurality of axial swirl vanes extending radially outward from the swirler body. At least one of the swirler body or vanes includes a spring channel defined therethrough. A fuel injector for a gas turbine engine can include an inner air swirler and/or outer air swirler as described above.

公开(公告)号：US20200018238A1

公开(公告)日：2020-01-16

申请号：US16031724

申请日：2018-07-10

Applicant: Delavan Inc.

Inventor： Jason A. Ryon ,  Lev Alexander Prociw ,  Gregory A. Zink ,  Joseph Samo

IPC: F02C7/22 ,  F23R3/10 ,  F23R3/28 ,  F02C7/228

Abstract: A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.

公开(公告)号：US20190309948A1

公开(公告)日：2019-10-10

申请号：US15949779

申请日：2018-04-10

Applicant: Delavan, Inc.

Inventor： Lev Alexander Prociw ,  Jason A. Ryon ,  Gregory A. Zink

IPC: F23R3/28 ,  F23R3/00 ,  F23R3/46

Abstract: A fuel injector for a multipoint injection system can include a body defining an air cavity for allowing air to flow therethrough and an interior cavity. A fuel is tube disposed at least partially within the interior cavity of the body. The fuel tube can include a first end configured to connect to a fuel injector connector of a fuel manifold, and a second end configured to connect to a fuel distributor of the fuel injector, wherein the fuel injector is configured to be disposed at least partially in a combustor dome. The fuel tube is configured to move in an axial direction to allow flexibility between the fuel manifold and the combustor dome.

公开(公告)号：US20190195498A1

公开(公告)日：2019-06-27

申请号：US15850175

申请日：2017-12-21

Applicant: Delavan Inc.

Inventor： Lev Alexander Prociw ,  Jason A. Ryon ,  Jacob Greenfield

IPC: F23R3/34 ,  F23R3/36

CPC classification number: F23R3/343 ,  F23R3/10 ,  F23R3/14 ,  F23R3/16 ,  F23R3/36

Abstract: A pilot nozzle for a dual fuel turbine engine includes an inner air circuit, a gaseous fuel circuit radially outward from the inner air circuit, a liquid fuel circuit radially outward from the inner air circuit, an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit, and a shroud radially outward from the outer air circuit. The shroud is configured to stabilize a pilot re-circulation zone downstream from outlets of the inner and outer air circuits and the liquid and gaseous fuel circuits.

公开(公告)号：US20190186750A1

公开(公告)日：2019-06-20

申请号：US15844216

申请日：2017-12-15

Applicant: Delavan, Inc.

Inventor： Lev Alexander Prociw ,  Jason A. Ryon ,  Jacob Greenfield

IPC: F23R3/36

Abstract: A method for assembling a fuel distribution system for a turbomachine fuel injector includes inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud and inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor. The method includes inserting a fuel transfer tube into an outer diameter of the shroud. The method includes brazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud.

公开(公告)号：US20190186364A1

公开(公告)日：2019-06-20

申请号：US15844282

申请日：2017-12-15

Applicant: Delavan Inc.

Inventor： Jacob Greenfield ,  Jason A. Ryon ,  Lev Alexander Prociw

IPC: F02C7/22 ,  F02C7/28 ,  F02C7/20

CPC classification number: F02C7/222 ,  F02C7/20 ,  F02C7/28 ,  F05D2230/60 ,  F05D2240/14 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2250/75 ,  F05D2260/941 ,  F23R3/34 ,  F23R3/343 ,  F23R2900/00005 ,  F23R2900/00018

Abstract: A turbomachine fuel injector system includes an air distributor configured to be mounted to and contained within a casing and to provide air to mix with a fuel from one or more fuel distribution systems. The system includes a fuel manifold configured to be mounted indirectly to the casing such that the fuel manifold system is contained within the casing but is independent such that fuel manifold does not touch or directly mount to either an interior of the casing or touch the air distributor within the casing to prevent or reduce thermal transfer from the air distributor to the fuel manifold.

公开(公告)号：US20190128528A1

公开(公告)日：2019-05-02

申请号：US16232168

申请日：2018-12-26

Applicant: Delavan Inc.

Inventor： Jason A. Ryon

IPC: F23R3/28 ,  F02C7/22

Abstract: A swirler includes a swirler body defining a longitudinal axis. A stack of swirler plates is assembled to the swirler body stacked in a direction along the longitudinal axis. Each of the swirl plates defines a vane portion. The swirler plates are mounted rotated circumferentially about the longitudinal axis relative to neighboring ones of the swirler plates so the vane portions form a swirler vane.

公开(公告)号：US20190024897A1

公开(公告)日：2019-01-24

申请号：US15656815

申请日：2017-07-21

Applicant: Delavan Inc.

Inventor： Lev A. Prociw ,  Jason A. Ryon ,  Gregory A. Zink

IPC: F23R3/14

Abstract: A nozzle assembly includes a fuel distributor for issuing a spray of fuel. A fuel conduit is in fluid communication with the fuel distributor and has a first end and a second end. The first end and/or the second end of the fuel conduit is operatively connected to the fuel distributor. The fuel conduit is configured to allow relative movement between the first end and the second end to accommodate dimensional variations of at least one of the nozzle assembly or a combustor. A nozzle system includes the nozzle assembly and a combustor wall having a nozzle inlet. The nozzle assembly is positioned adjacent to the nozzle inlet.

公开(公告)号：US20180283694A1

公开(公告)日：2018-10-04

申请号：US15472940

申请日：2017-03-29

Applicant: Delavan Inc.

Inventor： Jacob Greenfield ,  Thomas J. Ocken ,  Jason A. Ryon

IPC: F23R3/60 ,  F23R3/00

Abstract: An assembly for a turbomachine can include a fuel nozzle and a combustion liner. The fuel nozzle and the combustion liner can be attached to each using a plurality of clip joints such that the combustion liner is longitudinally fixed relative to the fuel nozzle but such that the combustion liner can radially move relative to the fuel nozzle.

公开(公告)号：US20180283692A1

公开(公告)日：2018-10-04

申请号：US15476362

申请日：2017-03-31

Applicant: Delavan Inc

Inventor： Jason A. Ryon ,  Lev A. Prociw ,  Gregory A. Zink

IPC: F23R3/28

Abstract: A combustor dome system includes an annular combustor dome defining a main axis therethrough. The combustor dome includes opposed upstream and downstream faces, wherein the upstream face is configured to face upstream toward a compressor discharge space, wherein the downstream face is configured to face downstream toward a combustor space. The downstream face has a curved cross-sectional profile. A plurality of nozzles extends at least partially through the combustor dome from the upstream face to the downstream face for injection of fuel into the combustor space. A fuel manifold is in fluid communication with the plurality of nozzles.