公开(公告)号：US09453646B2

公开(公告)日：2016-09-27

申请号：US14608342

申请日：2015-01-29

Applicant: General Electric Company

Inventor： Arjun Singh

IPC: F02C1/00 ,  F23R3/06 ,  F23R3/04

CPC classification number: F23R3/06 ,  F23R3/045

Abstract: An improved combustor is disclosed in which conventional combustion is changed to “rich to quench to lean” by changing the air entry arrangement in the liner of the combustor to remove mixing holes, reduce liner cooling and admit dilution air into the combustor liner in place of mixing air. In an alternative embodiment, dilution air is admitted into the combustor liner with the help of a plurality of pipes arranged so that air comes into the liner as a swirling flow in a direction opposite to nozzle swirl, so as to thereby produce a large mixing of air with the combustion gases and a resulting quenching effect, i.e., a rapid cooling of the combustion gases by quenching air. As such, the requirement for cooling water to quench the combustion gases is significantly reduced, thereby helping turbine efficiency and reducing turbine emissions.

Abstract translation: 公开了一种改进的燃烧器，其中通过改变燃烧器的衬套中的空气进入装置将常规燃烧改变为“富含冷却至急冷”，以除去混合孔，减少衬里冷却并将稀释空气进入燃烧器衬套，代替 混合空气 在替代实施例中，借助于布置多个管道的稀释空气被允许进入燃烧器衬套，使得空气以与喷嘴涡流相反的方向作为旋转流进入衬管，从而产生大的混合 具有燃烧气体的空气和产生的淬火效应，即通过骤冷空气快速冷却燃烧气体。 因此，冷却水淬火燃烧气体的要求显着降低，从而有助于涡轮机效率和减少涡轮机排放。

公开(公告)号：US20170356652A1

公开(公告)日：2017-12-14

申请号：US15180531

申请日：2016-06-13

Applicant: General Electric Company

Inventor： Arjun Singh ,  Scott Robert Simmons ,  Niranjana Giriyapura Thontadharya

IPC: F23R3/00 ,  F02C3/04 ,  F23R3/28 ,  F23R3/14 ,  F23R3/50

CPC classification number: F23R3/002 ,  F02C3/04 ,  F05D2220/32 ,  F23R3/14 ,  F23R3/283 ,  F23R3/50 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043

Abstract: The present application provides a combustor for a gas turbine engine. The combustor may include a number of fuel nozzles and an effusion plate assembly positioned about the fuel nozzles. The effusion plate assembly may include a cold pate, a hot plate, and a number of swirl inducing structures extending therebetween.

公开(公告)号：US09803864B2

公开(公告)日：2017-10-31

申请号：US14313198

申请日：2014-06-24

Applicant: General Electric Company

Inventor： Arjun Singh ,  Chandrasekhar Pushkaran ,  Nishant Govindbhai Parsania

IPC: F23R3/10 ,  F23R3/28 ,  F23R3/04 ,  F23R3/06

CPC classification number: F23R3/10 ,  F23R3/04 ,  F23R3/045 ,  F23R3/06 ,  F23R3/286

Abstract: A turbine combustor section has a flow conditioner including a plurality of conduits arranged to convey pressurized air to an air chamber for entrance into a plurality of fuel nozzles. Each conduit includes an inlet configured to receive the pressurized air from an annular passage and an outlet configured to deliver the pressurized air to the air chamber. A cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner.

公开(公告)号：US09739201B2

公开(公告)日：2017-08-22

申请号：US13889747

申请日：2013-05-08

Applicant: General Electric Company

Inventor： Chandrasekhar Pushkaran ,  Nishant Govindbhai Parsania ,  Arjun Singh

IPC: F02C7/22 ,  F23R3/00 ,  F23R3/06 ,  F23R3/16 ,  F23R3/34

CPC classification number: F02C7/22 ,  F23R3/005 ,  F23R3/06 ,  F23R3/16 ,  F23R3/346 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03043 ,  Y10T29/49229

Abstract: A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.

公开(公告)号：US20140331674A1

公开(公告)日：2014-11-13

申请号：US13889747

申请日：2013-05-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Chandrasekhar Pushkaran ,  Nishant Govindbhai Parsania ,  Arjun Singh

IPC: F02C7/22

CPC classification number: F02C7/22 ,  F23R3/005 ,  F23R3/06 ,  F23R3/16 ,  F23R3/346 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03043 ,  Y10T29/49229

Abstract: A wake reducing structure for a turbine system includes a combustor liner having an inner surface and an outer surface, the inner surface defining a combustor chamber. Also included is an airflow path located along the outer surface of the combustor liner. Further included is a wake generating component disposed in the airflow path and proximate the combustor liner, wherein the wake generating component generates a wake region located downstream of the wake generating component. Yet further included is an airfoil at least partially disposed in the wake region, the airfoil comprising at least one airfoil hole.

Abstract translation: 涡轮机系统的尾流减少结构包括具有内表面和外表面的燃烧器衬套，内表面限定燃烧室。 还包括沿着燃烧器衬套的外表面设置的气流路径。 进一步包括设置在气流路径中并且靠近燃烧器衬套的尾流产生部件，其中，尾流产生部件产生位于尾流产生部件下游的尾流区域。 还包括至少部分地设置在尾流区域中的翼型件，翼型件包括至少一个翼型孔。