公开(公告)号：US20230194090A1

公开(公告)日：2023-06-22

申请号：US17672946

申请日：2022-02-16

Applicant: General Electric Company

Inventor： Ramal Janith Samarasinghe ,  Fei Han ,  Krishnakumar Venkatesan

IPC: F23M20/00 ,  F23R3/28 ,  F02C7/22

CPC classification number: F23M20/005 ,  F23R3/286 ,  F02C7/222 ,  F23R2900/00014 ,  F05D2240/35 ,  F05D2260/963

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a combustion chamber, a compressed air passage fluidly coupled to the combustion chamber, and a swirler. At least one acoustic resonator can be provided in the combustor.

公开(公告)号：US20190017441A1

公开(公告)日：2019-01-17

申请号：US15651088

申请日：2017-07-17

Applicant: General Electric Company

Inventor： Krishnakumar Venkatesan ,  Narendra Digamber Joshi

IPC: F02C7/262 ,  F23R3/00 ,  F02D37/02

Abstract: A gas turbine engine combustor includes a dome plate, an inner liner, and an outer liner. The inner liner and the outer liner are separately coupled to a rear side of the dome plate and both extend rearward therefrom. The outer and inner liners define an annular combustion chamber therebetween that extends rearward from the dome plate. At least one of the outer liner or the dome plate includes an igniter cavity formed therein that is separated from the combustion chamber by a partition wall. The partition wall defines one or more transfer holes therethrough that fluidly connect the igniter cavity to the combustion chamber.

公开(公告)号：US20130145771A1

公开(公告)日：2013-06-13

申请号：US13758197

申请日：2013-02-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ahmed Mostafa ELKady ,  Narendra Digamber Joshi ,  Parag Prakash Kulkarni ,  Christian Lee Vandervort ,  Krishnakumar Venkatesan

IPC: F02C3/20

CPC classification number: F02C3/20 ,  F02C3/22 ,  F23C2900/99011 ,  F23L7/00 ,  F23L2900/07002 ,  F23L2900/07005 ,  F23R3/346 ,  F23R2900/00002 ,  Y02E20/16 ,  Y02E20/344 ,  Y02T50/678

Abstract: A system and method of reducing gas turbine nitric oxide emissions includes a first combustion stage configured to burn air vitiated with diluents to generate first combustion stage products. A second combustion stage is configured to burn the first combustion stage products in combination with enriched oxygen to generate second combustion stage products having a lower level of nitric oxide emissions than that achievable through combustion with vitiated air alone or through combustion staging alone.

Abstract translation: 一种减少燃气轮机一氧化氮排放的系统和方法包括：第一燃烧阶段，其被配置为燃烧用稀释剂残留的空气以产生第一燃烧级产物。 第二燃烧阶段被配置为燃烧第一燃烧阶段产物与富氧组合以产生具有比单独的燃烧燃烧单独或仅通过燃烧分段可燃的一氧化氮排放低的第二燃烧级产物。