-
公开(公告)号：US08844294B2
公开(公告)日：2014-09-30
申请号：US14248444
申请日：2014-04-09
Applicant: United Technologies Corporation
Inventor： Stephen A. Morford , Michael J. Larkin
CPC classification number: F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly that includes an inlet lip section and an inlet internal diffuser section downstream of the inlet lip section. A variable area fan nozzle is positioned near an aft segment of the nacelle assembly, the variable area fan nozzle adaptable to move between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area. At least one boundary layer control device is positioned near one of the inlet lip section and the inlet internal diffuser section. A controller is configured to move the variable area fan nozzle from the first position to the second position and to actuate the at least one boundary layer control device to introduce an airflow in response to an operability condition.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括机舱组件，其包括入口唇部和入口唇部的下游的入口内部扩散器部分。 可变区域风扇喷嘴位于机舱组件的后段附近，可变区域风扇喷嘴适于在具有第一排放气流区域的第一位置和具有大于第一排出气流的第二排放气流区域的第二位置之间移动 区。 至少一个边界层控制装置位于入口唇部和入口内部扩散器部分中的一个附近。 控制器被配置为将可变区域风扇喷嘴从第一位置移动到第二位置，并且致动至少一个边界层控制装置以响应于可操作性条件引入气流。
-
公开(公告)号：US20200232390A1
公开(公告)日：2020-07-23
申请号：US16251492
申请日：2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
-
公开(公告)号：US11346282B2
公开(公告)日：2022-05-31
申请号：US16251492
申请日：2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
-
公开(公告)号：US20140216002A1
公开(公告)日：2014-08-07
申请号：US14248444
申请日：2014-04-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Stephen A. Morford , Michael J. Larkin
CPC classification number: F02K1/165 , F02K1/06 , F02K1/15 , F02K3/06 , F05D2260/80 , F05D2270/09 , F05D2270/092 , Y02T50/671 , Y10T29/4932 , Y10T137/0536
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly that includes an inlet lip section and an inlet internal diffuser section downstream of the inlet lip section. A variable area fan nozzle is positioned near an aft segment of the nacelle assembly, the variable area fan nozzle adaptable to move between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area. At least one boundary layer control device is positioned near one of the inlet lip section and the inlet internal diffuser section. A controller is configured to move the variable area fan nozzle from the first position to the second position and to actuate the at least one boundary layer control device to introduce an airflow in response to an operability condition.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括机舱组件，其包括入口唇部和入口唇部的下游的入口内部扩散器部分。 可变区域风扇喷嘴位于机舱组件的后段附近，可变区域风扇喷嘴适于在具有第一排放气流区域的第一位置和具有大于第一排出气流的第二排放气流区域的第二位置之间移动 区。 至少一个边界层控制装置位于入口唇部和入口内部扩散器部分中的一个附近。 控制器构造成将可变区域风扇喷嘴从第一位置移动到第二位置，并且致动至少一个边界层控制装置以响应于可操作性条件引入气流。
-
-
-
Search Results
4
records
(took 0.014 seconds)
