-
公开(公告)号：US12065989B2
公开(公告)日：2024-08-20
申请号：US17977292
申请日：2022-10-31
IPC分类号： B64C11/48 , F02K3/06 , B64C11/00 , B64C11/18 , F01D9/02 , F01D17/10 , F01D17/14 , F02C7/36 , F02K3/065 , F02K3/072 , F04D19/02 , F04D29/34 , F04D29/38
CPC分类号： F02K3/06 , B64C11/001 , B64C11/18 , B64C11/48 , F01D9/02 , F01D17/105 , F01D17/14 , F02C7/36 , F02K3/065 , F02K3/072 , F04D19/02 , F04D29/34 , F04D29/388 , F05D2200/14 , F05D2200/211 , F05D2220/323
摘要： A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R1, a primary fan hub radius R2, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R3, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of R1 to R3 equals
R
1
R
3
=
(
EFP
)
(
1
-
RqR
(
Sec
.
-
Fan
)
2
)
(
1
-
RqR
Prim
.
-
Fan
2
)
(
T
P
T
S
)
(
EBA
)
.-
公开(公告)号：US12060804B2
公开(公告)日：2024-08-13
申请号：US17485463
申请日：2021-09-26
发明人： Karel Mizerovsky , Pavel Stepanek , Jan Klement , Adam Ohnút
CPC分类号： F01D25/24 , F01D9/02 , F05D2220/40 , F05D2230/21 , F05D2250/38
摘要： A turbine housing can include a bearing housing end and a treatment unit end; a volute wall that defines a volute; a wall that defines at least a portion of a turbine wheel space that defines a turbine wheel space axis and a turbine wheel space diameter, where the wall extends to an axial peak to define an extended space with an extended space outlet having an extended space outlet dimension; and an outlet wall that defines an outlet space with a treatment unit end outlet having an outlet dimension, where the extended space is disposed at least in part axially between the turbine wheel space and the outlet space to increase axial velocity uniformity at the treatment unit end outlet.
-
公开(公告)号：US12037927B2
公开(公告)日：2024-07-16
申请号：US18032054
申请日：2022-03-30
CPC分类号： F01D9/02 , F01D5/147 , F01D25/32 , F05D2220/31 , F05D2250/294
摘要： A turbine stator vane includes: a stator vane body extending in a radial direction intersecting a flow direction of steam; a recovery portion that is defined on a surface of the stator vane body, and configured to recover a liquid film flowing along the surface of the stator vane body; and a center region, which is defined on the surface of the stator vane body and includes grooves extending from an upstream side toward the recovery portion in the flow direction. Intervals between adjacent grooves decrease from the upstream side toward the recovery portion.
-
公开(公告)号：US11982195B2
公开(公告)日：2024-05-14
申请号：US17604170
申请日：2020-04-14
CPC分类号： F01D25/02 , F01D9/02 , F05D2220/323 , F05D2230/31 , F05D2240/128
摘要： A splitter between a primary flow and a secondary flow of a dual flow turbomachine includes a single-piece structure including an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle.
-
公开(公告)号：US11970946B2
公开(公告)日：2024-04-30
申请号：US17388228
申请日：2021-07-29
发明人： Travis J. Packer , James Hamilton Grooms , David Fasig , Richard William Jendrix , Scott Alan Schimmels , Bradford Alan Tracey , Michael Alan Hile , Thomas Ryan Wallace
CPC分类号： F01D11/24 , F01D9/02 , F01D25/243 , F05D2240/126 , F05D2240/55
摘要： A clearance control assembly for a gas turbine engine that defines an axial direction and a radial direction and includes a stage of rotor blades and a shroud hanger. The assembly includes a case configured to be positioned outward along the radial direction from the stage of rotor blades when installed in the gas turbine engine. The case is further configured to be engaged with the shroud hanger at a first location when installed in the gas turbine engine. The assembly also includes a baffle positioned outward along the radial direction from the case to define a chamber therebetween. The baffle has a forward end and an aft end. The forward end of the baffle is engaged with the case to form a first seal and the aft end of the baffle is engaged with the case to form a second seal. The baffle, the case, or both define an inlet to allow a fluid to enter the chamber and the case defines an outlet to allow the fluid to exit the chamber.
-
公开(公告)号：US20240102398A1
公开(公告)日：2024-03-28
申请号：US18370528
申请日：2023-09-20
申请人： MTU Aero Engines AG
CPC分类号： F01D11/001 , F01D9/02 , F05D2220/323 , F05D2240/12 , F05D2240/55
摘要： A module for a turbomachine, including a guide blade arrangement, a seal carrier that is situated radially within an inner platform of the guide blade arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding body as well as a connecting element. The seal carrier walls have a multipart design with respect to one another, and the second seal carrier wall is fastened to the first seal carrier wall and to the seal carrier via the connecting element. The sliding body holds the seal carrier walls at a distance from one another in such a way that they mutually axially delimit a clearance in which the guide blade arrangement engages via a radially inwardly extending guide pin. A radially inner section of the second seal carrier wall has frictional contact relative to the seal carrier.
-
公开(公告)号：US11939878B1
公开(公告)日：2024-03-26
申请号：US18081924
申请日：2022-12-15
发明人： Jonathan Dwight Berry , Emily Kaufman , Clay Thomas Griffis , Bailey Basso , Archie Lee Swanner, Jr.
摘要： A turbomachine component is provided. The turbomachine component formed from an additive manufacturing system. The additive manufacturing system defines an axial build direction, a radial direction, and a circumferential direction. The turbomachine component includes an exterior portion. The exterior portion includes a first end wall, a second end wall, and an outer band extending axially between the first end wall and the second end wall. The turbomachine component further includes an interior portion disposed within the exterior portion. The interior portion includes a self-breaking inner band extending axially between the first end wall and the second end wall. The self-breaking inner band includes a plurality of teeth disposed between the first end wall and the second end wall.
-
8.发明授权公开(公告)号：US11885229B2
公开(公告)日：2024-01-30
申请号：US17026887
申请日：2020-09-21
IPC分类号： H02K9/20 , H02K5/20 , F04D29/58 , F01D25/26 , F01D25/12 , F01D9/02 , F01D1/04 , H02K9/19 , B64D27/24 , B64D27/02
CPC分类号： F01D25/12 , F01D1/04 , F01D9/02 , F01D25/26 , F04D29/5806 , H02K5/207 , H02K9/19 , H02K9/20 , B64D27/24 , B64D2027/026 , F05D2220/323 , F05D2260/20
摘要： The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit.
-
公开(公告)号：US20230392510A1
公开(公告)日：2023-12-07
申请号：US18032054
申请日：2022-03-30
CPC分类号： F01D9/02 , F01D25/32 , F01D5/147 , F05D2220/31 , F05D2250/294
摘要： A turbine stator vane comprising: a stator vane body extending in a radial direction intersecting the flow direction of steam; a recovery portion that is formed on the surface of the stator vane body, and recovers a liquid film flowing along the surface; and a center region, which is formed on the surface of the stator vane body and in which a plurality of first fine grooves extending from the upstream side toward the recovery portion in the flow direction are formed, wherein the interval between adjacent first fine grooves narrows from the upstream side toward the recovery portion.
-
公开(公告)号：US11808156B2
公开(公告)日：2023-11-07
申请号：US17662537
申请日：2022-05-09
申请人： IHI Corporation
发明人： Daisuke Nishii , Masaaki Hamabe
CPC分类号： F01D11/08 , F01D9/02 , F05D2220/30 , F05D2240/12 , F05D2240/55
摘要： A secondary flow suppression structure includes: a turbine rotor blade including an outer shroud; a turbine stator vane located rearward of the turbine rotor blade and including an outer band; a seal surface facing the outer shroud at a radial outside of the outer shroud; a fin projecting from the outer shroud toward the seal surface; and a cavity formed between the seal surface and the turbine stator vane, formed in an annular shape extending in a circumferential direction, and provided with an opening portion opening radially inward on a virtual surface of the seal surface extending rearward. A front end of the outer band is positioned at the same height as the virtual surface in a radial direction, or positioned radially inward of the virtual surface.
-
-
-
-
-
-
-
-
-
搜索结果
1530 条记录 (耗时 0.019 秒)
