公开(公告)号：WO2014074190A2

公开(公告)日：2014-05-15

申请号：PCT/US2013/054944

申请日：2013-08-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： PRAISNER, Thomas, J. ,  AGGARWALA, Andrew, S. ,  NASH, Timothy, Charles ,  ALLEN-BRADLEY, Eunice ,  GROVER, Eric, A.

IPC: F01D5/14 ,  F01D9/02

CPC classification number: F01D9/02 ,  F01D5/143 ,  F01D5/145 ,  F04D29/324 ,  F04D29/542 ,  F04D29/681 ,  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 airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.

Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁，以及从端壁径向突出的多个翼型件。 每个翼型可以具有在前缘和后缘之间沿弦轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上沿圆周间隔开，从而在相邻翼型件之间限定多个流动通道。 翼型阵列可进一步包括从靠近所述多个翼型中的至少一个的前缘附近的所述多个翼型中的至少一个翼型的第一侧的端壁延伸的凸形轮廓区域以及位于所述翼型中的凹形轮廓区域 端壁并延伸跨过所述多个流动通道中的所述至少一个。

公开(公告)号：WO2014070280A2

公开(公告)日：2014-05-08

申请号：PCT/US2013/054953

申请日：2013-08-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： PRAISNER, Thomas, J. ,  AGGARWALA, Andrew, S. ,  GROVER, Eric, A. ,  JUREK, Renee, J.

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，以及从端壁径向突出的多个翼型件。 每个翼型可以具有在前缘和后缘之间沿弦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的第一侧并且在所述多个翼型中的至少一个的前缘附近的端壁延伸的凸起轮廓区域。 翼型阵列可以进一步包括端壁中的凹形轮廓区域，所述凹形轮廓区域邻近所述多个翼型中的所述至少一个的第一侧和凸形轮廓区域的后部。

公开(公告)号：WO2013169711A1

公开(公告)日：2013-11-14

申请号：PCT/US2013/039850

申请日：2013-05-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： GROVER, Eric, A. ,  PRAISNER, Thomas, J. ,  WAGNER, Joel, H.

IPC: F02C7/28 ,  F02D7/00 ,  F01D11/10 ,  F01D25/00

CPC classification number: F01D11/001 ,  F01D5/081 ,  F01D11/02 ,  F05D2250/73 ,  F05D2260/97

Abstract: Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.

Abstract translation: 涡轮机械，例如燃气涡轮发动机，具有相对的第一和第二表面的部件，并且在表面之间具有空腔，并且第一表面相对于第二表面移动。 涡轮机械还具有用于产生并入第一和第二表面的压力变化的至少一个特征。