公开(公告)号：US20170356654A1

公开(公告)日：2017-12-14

申请号：US15177825

申请日：2016-06-09

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Justin M. Locke ,  Dennis Moura ,  Duane McCormick ,  Scott A. Liljenberg ,  Theodore Strickland ,  William Proscia

IPC分类号： F23R3/28 ,  F23R3/06 ,  F23R3/50 ,  F23R3/12

CPC分类号： F23R3/28 ,  F23D11/38 ,  F23K5/06 ,  F23R3/06 ,  F23R3/12 ,  F23R3/14 ,  F23R3/346 ,  F23R3/50 ,  F23R2900/00014 ,  F23R2900/03042 ,  Y02T50/675

摘要： A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.

公开(公告)号：US11598527B2

公开(公告)日：2023-03-07

申请号：US15177825

申请日：2016-06-09

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Justin M. Locke ,  Dennis Moura ,  Duane McCormick ,  Scott A. Liljenberg ,  Theodore Strickland ,  William Proscia

IPC分类号： F23R3/28 ,  F23D11/38 ,  F23R3/34 ,  F23K5/06 ,  F23R3/14 ,  F23R3/06 ,  F23R3/12 ,  F23R3/50

摘要： A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.

公开(公告)号：US11378275B2

公开(公告)日：2022-07-05

申请号：US16705547

申请日：2019-12-06

申请人： United Technologies Corporation

发明人： Justin M. Locke ,  Timothy S. Snyder ,  William Proscia

IPC分类号： F23R3/28 ,  F23R3/14 ,  F23R3/30

摘要： An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.

公开(公告)号：US20210172604A1

公开(公告)日：2021-06-10

申请号：US16705547

申请日：2019-12-06

申请人： United Technologies Corporation

发明人： Justin M. Locke ,  Timothy S. Snyder ,  William Proscia

IPC分类号： F23R3/14 ,  F23R3/28

摘要： An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.