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公开(公告)号：US09995157B2
公开(公告)日：2018-06-12
申请号：US14675824
申请日：2015-04-01
Applicant: United Technologies Corporation
Inventor： James P. Bangerter
CPC classification number: F01D9/02 , F01D1/02 , F01D5/02 , F01D5/18 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/232 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil that extends radially from a first side of a platform. A pocket is provided in the platform on a second side opposite the airfoil. Forward and aft rails extend from the second side of the platform. One of the forward and aft rails includes a radial surface. An impingement plate is secured to the platform over the pocket. The impingement plate includes a radial flange that engages the radial surface.
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公开(公告)号：US20160265784A1
公开(公告)日：2016-09-15
申请号：US15032354
申请日：2014-08-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James P. Bangerter , Kevin J. Low
Abstract: A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.
Abstract translation: 燃气涡轮发动机内的衬板包括从冷侧限定第一高度的周边轨道。 衬板还包括中间轨道，该中间轨道从冷侧限定第二高度，其中第二高度小于第一高度。
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公开(公告)号：US20160169515A1
公开(公告)日：2016-06-16
申请号：US14908751
申请日：2014-08-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John S. Tu , James P. Bangerter , Robert Sze , James B. Hoke , Monica Pacheco-Tougas
CPC classification number: F23R3/06 , F02C7/18 , F23R3/002 , F23R3/005 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A combustor panel an increased cooling holes provided at at least one of a pair of circumferential edges, a leading edge, a trailing edge or a hole circumference. The increase may be defined as a reduction in spacing or an increase in density. In another feature, holes at the circumferential edges may extend outwardly to an outlet in alignment with rails.
Abstract translation: 燃烧器面板具有设置在一对周向边缘，前缘，后缘或孔圆周中的至少一个上的增加的冷却孔。 增加可以被定义为间隔的减小或密度的增加。 在另一个特征中，圆周边缘处的孔可以向外延伸到与轨道对准的出口。
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公开(公告)号：US20150241063A1
公开(公告)日：2015-08-27
申请号：US14432527
申请日：2013-03-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James P. Bangerter , Kevin Joseph Low , Jonathan M. Jause , Robert Sonntag , Reza Rezvani , David Kwoka
CPC classification number: F23R3/005 , F02C7/18 , F23R3/002 , F23R3/06 , F23R3/46 , F23R3/50 , F23R2900/00017 , F23R2900/03043 , F23R2900/03045 , Y02T50/675
Abstract: A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.
Abstract translation: 燃烧器包括限定燃烧室的至少一部分的壳体。 壳体包括具有通向燃烧室的孔口的壁。 索环包括从主体部分突出的主体部分和唇部。 身体部分和唇部具有围绕通过索环的通道延伸的表面。 唇缘的至少一部分在壳的壁的孔口内延伸。
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公开(公告)号：US10808937B2
公开(公告)日：2020-10-20
申请号：US15032354
申请日：2014-08-29
Applicant: United Technologies Corporation
Inventor： James P. Bangerter , Kevin J. Low
Abstract: A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.
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Patent Agency Ranking
公开(公告)号：US10760500B2
公开(公告)日：2020-09-01
申请号：US15913105
申请日：2018-03-06
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Donald W. Peters , James P. Bangerter
Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.
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公开(公告)号：US10088162B2
公开(公告)日：2018-10-02
申请号：US14432527
申请日：2013-03-12
Applicant: United Technologies Corporation
Inventor： James P. Bangerter , Kevin Joseph Low , Jonathan M. Jause , Robert Sonntag , Reza Rezvani , David Kwoka
Abstract: A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.
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18.发明申请公开(公告)号：US20160348590A1
公开(公告)日：2016-12-01
申请号：US14727475
申请日：2015-06-01
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Donald W. Peters , James P. Bangerter
CPC classification number: F02C7/28 , F02C3/04 , F02K1/805 , F05D2220/32 , F05D2240/55 , F05D2240/58 , F05D2250/14 , F05D2250/314 , F05D2250/34 , F05D2250/41 , F05D2260/38 , F05D2260/57 , F05D2300/603 , F05D2300/6034 , F16J15/3488 , Y02T50/672
Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.
Abstract translation: 提供密封系统。 密封系统可以包括具有环形几何形状的第一管道，在径向方向上与第一管道重叠的第二管道以及设置在第一管道和第二管道之间的密封件。 密封件可以包括由第一管道限定的凹槽和构造成可滑动地接合凹槽的活塞。
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公开(公告)号：US20160010559A1
公开(公告)日：2016-01-14
申请号：US14770341
申请日：2014-02-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James B. Hoke , James P. Bangerter
IPC: F02C7/25
CPC classification number: F02C7/25 , F05D2220/32 , F05D2240/35 , F05D2260/231 , F23R3/002 , F23R2900/00004 , F23R2900/00012 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: A heat shield for a combustor of a gas turbine engine includes a cold side opposite a hot side, the cold side defines a grommet that surrounds an igniter aperture, the grommet includes a multiple of fins.
Abstract translation: 用于燃气涡轮发动机的燃烧器的隔热罩包括与热侧相对的冷侧，冷侧限定围绕点火器孔的索环，护环包括多个翅片。
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公开(公告)号：US20150285086A1
公开(公告)日：2015-10-08
申请号：US14675824
申请日：2015-04-01
Applicant: United Technologies Corporation
Inventor： James P. Bangerter
CPC classification number: F01D9/02 , F01D1/02 , F01D5/02 , F01D5/18 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/232 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: A stator vane for a gas turbine engine includes an airfoil that extends radially from a first side of a platform. A pocket is provided in the platform on a second side opposite the airfoil. Forward and aft rails extend from the second side of the platform. One of the forward and aft rails includes a radial surface. An impingement plate is secured to the platform over the pocket. The impingement plate includes a radial wall that engages the radial surface.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括从平台的第一侧径向延伸的翼型件。 在与翼型相对的第二侧的平台上设置有口袋。 前后导轨从平台的第二侧延伸。 前后轨道中的一个包括径向表面。 冲击板在口袋上固定到平台上。 冲击板包括接合径向表面的径向壁。
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