公开(公告)号：US20150354365A1

公开(公告)日：2015-12-10

申请号：US14728514

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Wolfgang Balzer ,  Thomas J. Praisner ,  Atul Kohli ,  Mark F. Zelesky ,  Dominic J. Mongillo, JR.

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/02

Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.

Abstract translation: 用于燃气涡轮发动机的翼型件包括具有压力和吸力侧面的翼型件，其在前缘和后缘处接合。 翼型件从支撑件沿径向方向延伸跨度。 0％跨度和100％跨度位置分别对应于支撑件和末端处的翼型。 前缘和后缘在轴向上彼此间隔开一个轴向弦。 在跨距位置处的翼型件的横截面具有与压力侧和吸力侧相切的直径。 直径对应于横截面内最大的圆形配件。 直径与轴向弦的比例在50％至95％的跨度位置之间至少为0.4。

公开(公告)号：US20150285157A1

公开(公告)日：2015-10-08

申请号：US14615665

申请日：2015-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew D. Burdick ,  Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Hudson ,  Michael G. McCaffrey

IPC: F02C9/20 ,  F02C3/04

CPC classification number: F02C9/20 ,  F01D5/148 ,  F01D9/02 ,  F01D11/025 ,  F01D17/162 ,  F02C3/04 ,  F05D2240/122 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T137/0536

Abstract: One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion.

Abstract translation: 本公开的一个示例性实施例涉及一种包括具有静态部分，可移动部分以及静态部分和可移动部分之间的密封件的翼型的系统。 密封件可与静态部分和可移动部分分开地移动。

公开(公告)号：US20140090401A1

公开(公告)日：2014-04-03

申请号：US13663977

申请日：2012-10-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Grover ,  Renee J. Jurek

IPC: F01D9/00 ,  F02C3/04

CPC classification number: F01D5/145 ,  F01D5/143 ,  F04D29/324 ,  F04D29/329 ,  F04D29/547 ,  F04D29/681 ,  F05D2240/123 ,  F05D2240/305 ,  F05D2250/712 ,  Y02T50/673

Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。 所述翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和所述凸形轮廓区域的后部的所述端壁中的凹形轮廓区域。