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：US20180274785A1

公开(公告)日：2018-09-27

申请号：US15992470

申请日：2018-05-30

Applicant: Delavan Inc

Inventor： Lev Alexander Prociw ,  Timothy Griffith

IPC: F23R3/28 ,  F02C7/224 ,  F23R3/34 ,  F23D14/78 ,  F02C7/22 ,  F02C7/228

CPC classification number: F23R3/283 ,  F02C7/222 ,  F02C7/224 ,  F02C7/228 ,  F05D2260/232 ,  F23D14/78 ,  F23D2214/00 ,  F23R3/346

Abstract: A fuel system includes a fuel supply system. A plurality of fuel nozzles are connected in fluid communication with the fuel supply system to supply fuel from a fuel source to be issued for combustion from the fuel nozzles. A cooling system is included, wherein at least one of the fuel nozzles includes a cooling circuit in addition to a fuel circuit for issuing fuel from the fuel supply system for combustion. The cooling circuit includes an inlet and an outlet. The inlet is in fluid communication with the cooling system for circulation of coolant through the cooling circuit and back to the cooling system out the outlet of the cooling circuit for cooling the fuel circuit with the fuel circuit staged off.

公开(公告)号：US20180178229A1

公开(公告)日：2018-06-28

申请号：US15904624

申请日：2018-02-26

Applicant: Delavan Inc

Inventor： Jason A. Ryon ,  Philip E. O. Buelow ,  Steven L. Smith ,  Lev Alexander Prociw

IPC: B05B7/10 ,  F02C7/232 ,  F23R3/04 ,  F23R3/14 ,  F23R3/28 ,  F23D11/10

CPC classification number: B05B7/10 ,  F02C7/232 ,  F05D2220/32 ,  F23D11/107 ,  F23R3/04 ,  F23R3/14 ,  F23R3/286

Abstract: An atomizer includes an atomizer body with a plurality of air passages defined therethrough from an upstream end of the atomizer body to a downstream end thereof. The air passages together define an air circuit through the atomizer body. A fuel circuit is defined in the atomizer body extending from a fuel inlet to a respective fuel outlet opening into each air passage. The air passages can be arranged circumferentially about a central axis defined by the atomizer body. The fuel circuit can include a manifold extending circumferentially about the atomizer body in fluid communication with a fuel opening in each respective air passage.

公开(公告)号：US20180080384A1

公开(公告)日：2018-03-22

申请号：US15268211

申请日：2016-09-16

Applicant: Delavan Inc

Inventor： Lev Alexander Prociw ,  Jason A. Ryon

IPC: F02C7/22 ,  B05B1/34 ,  B05B7/10

CPC classification number: F02C7/222 ,  B05B1/341 ,  B05B7/10 ,  F05D2220/32 ,  F23D14/78 ,  F23R3/283

Abstract: A nozzle includes a nozzle body defining a liquid circuit extending from a liquid inlet to a liquid outlet. The liquid circuit includes a plurality of spiral liquid passages spiraling radially inward relative to a spray axis. The spiral liquid passages all lie in a plane normal to the spray axis. A manifold assembly includes a plurality of such nozzles. A manifold ring is in fluid communication with the liquid inlet of each of the nozzles to deliver liquid to the nozzles. The nozzles are circumferentially spaced apart around the manifold ring.

公开(公告)号：US09897321B2

公开(公告)日：2018-02-20

申请号：US14674580

申请日：2015-03-31

Applicant: Delavan Inc

Inventor： Lev Alexander Prociw

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34 ,  F23D11/10 ,  F23D11/38 ,  F23C7/00 ,  F23R3/12

CPC classification number: F23R3/286 ,  F23C7/002 ,  F23C7/004 ,  F23D11/107 ,  F23D11/383 ,  F23R3/12 ,  F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R3/346

Abstract: A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body includes an air passage having a radial swirler and a converging conical cross-section. A fuel circuit is radially outboard from the air passage with respect to the longitudinal axis. The fuel circuit extends from a fuel circuit inlet to a fuel circuit annular outlet. The fuel circuit includes a plurality of helical passages to mitigate gravitational effects at low fuel flow rates. Each helical passage of the fuel circuit opens tangentially with respect to the fuel circuit annular outlet into an outlet of the air passage.

公开(公告)号：US11635210B2

公开(公告)日：2023-04-25

申请号：US17125028

申请日：2020-12-17

Applicant: Delavan Inc.

Inventor： Jason Ryon ,  Gregory Zink ,  Lev Alexander Prociw

IPC: F23R3/28 ,  F02C7/24 ,  F02C7/22

Abstract: A heat shielded assembly includes a fuel structure of a combustor of a gas turbine engine and a woven heat shield at least partially conformally surrounding the fuel structure and spaced from an exterior of the fuel structure by a distance where it surrounds the fuel structure. The fuel structure is configured to deliver fuel to the combustor. The woven heat shield comprises a first set of strands, a second set of strands interwoven with the first set of strands, and a weave pattern comprising the first set of strands and the second set of strands. Each strand of the first set of strands extends in a first direction, each strand of the second set of strands extends in a second direction transverse to the first direction, and the first set of strands and the second set of strands are not attached where they intersect in the weave pattern.

公开(公告)号：US11525580B2

公开(公告)日：2022-12-13

申请号：US17125114

申请日：2020-12-17

Applicant: Delavan Inc.

Inventor： Jason Ryon ,  Brandon P. Williams ,  Lev Alexander Prociw

IPC: F23R3/34 ,  F02C7/264 ,  F02C7/266 ,  F23R3/28 ,  F02C7/22 ,  F23R3/42

Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.

公开(公告)号：US11525404B2

公开(公告)日：2022-12-13

申请号：US17089236

申请日：2020-11-04

Applicant: Delavan Inc.

Inventor： Jason Ryon ,  Lev Alexander Prociw

IPC: F02C7/264 ,  F02C7/18 ,  F23R3/06

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.

公开(公告)号：US11473505B2

公开(公告)日：2022-10-18

申请号：US17089250

申请日：2020-11-04

Applicant: Delavan Inc.

Inventor： Jason Ryon ,  Lev Alexander Prociw

IPC: F02C7/00 ,  F02C7/264 ,  F23R3/06 ,  F23D14/78 ,  B33Y80/00

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.