公开(公告)号：US11913468B2

公开(公告)日：2024-02-27

申请号：US18136110

申请日：2023-04-18

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason A. Ryon ,  Jacob Greenfield ,  Adrian L. Stoicescu

IPC: F04D29/32 ,  F02K5/00 ,  F04D29/22 ,  F04D29/24 ,  F04D29/28 ,  F04D29/30

CPC classification number: F04D29/32 ,  F02K5/00 ,  F05D2230/31

Abstract: A method of making an impeller includes building the impeller in a layer by layer process in a build direction along the rotational axis starting from a base of the hub. The plurality of blades includes a plurality of perforated blades that support the shroud during additively manufacturing the impeller. The method can include installing the impeller in a fuel pump, air compressor, or the like, without removing the perforated blades from the impeller.

公开(公告)号：US20230304666A1

公开(公告)日：2023-09-28

申请号：US18098793

申请日：2023-01-19

Applicant: Collins Engine Nozzles, Inc.

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

IPC: F23R3/34 ,  F23R3/36 ,  F23R3/14

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

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：US11846425B2

公开(公告)日：2023-12-19

申请号：US18098793

申请日：2023-01-19

Applicant: Collins Engine Nozzles, Inc.

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

IPC: F23R3/34 ,  F23R3/36 ,  F23R3/14 ,  F23R3/16 ,  F23R3/10

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

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：US20230258198A1

公开(公告)日：2023-08-17

申请号：US18136110

申请日：2023-04-18

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason A. Ryon ,  Jacob Greenfield ,  Adrian L. Stoicescu

IPC: F04D29/32

CPC classification number: F04D29/32 ,  F02K5/00

Abstract: A method of making an impeller includes building the impeller in a layer by layer process in a build direction along the rotational axis starting from a base of the hub. The plurality of blades includes a plurality of perforated blades that support the shroud during additively manufacturing the impeller. The method can include installing the impeller in a fuel pump, air compressor, or the like, without removing the perforated blades from the impeller.

公开(公告)号：US11774102B2

公开(公告)日：2023-10-03

申请号：US17336610

申请日：2021-06-02

Applicant: Collins Engine Nozzles, Inc.

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

IPC: F23R3/60 ,  F23R3/28 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R3/283 ,  F23R2900/00005

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：US11674689B2

公开(公告)日：2023-06-13

申请号：US17458240

申请日：2021-08-26

Applicant: Collins Engine Nozzles, Inc.

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

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34 ,  F23R3/12

CPC classification number: F23R3/286 ,  F23R3/12 ,  F23R3/14 ,  F23R3/343

Abstract: An air mixer includes an annular body defining a center axis. A plurality of slots are defined in the annular body circumferentially spaced apart from one another. Each slot defines a respective center injection axis extending from an outer surface of the annular body to an inner surface of the annular body. Each respective center injection axis is parallel to a respective plane bisecting the annular body. At least one of the slots is intersected by the respective bisecting plane parallel to its respective center injection axis.