公开(公告)号：JP2003138905A

公开(公告)日：2003-05-14

申请号：JP2002269736

申请日：2002-09-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  CHON YOUNG H ,  DUBE BRYAN P

IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

Abstract: PROBLEM TO BE SOLVED: To provide an airfoil having an improved cooling mechanism. SOLUTION: An airfoil part of a turbine includes internal cavities 52, 54 and a plurality of indentations 90 disposed on inside surfaces 38 of the internal cavities. By the dents 90, heat transfer is improved to cool the internal cavities 52, 54 of the airfoil to elongate the service life of the airfoil, and the amount of compressor bleed air required is reduced to optimize engine efficiency. The advantage of such a cooling mechanism is that it does not restrict a cooling flow in the internal cavities 52, 54. The indentations 90 may have variable patterns or different geometric shapes.

公开(公告)号：WO2006025847A3

公开(公告)日：2006-05-26

申请号：PCT/US2005000784

申请日：2005-01-07

Applicant: UNITED TECHNOLOGIES CORP ,  MONGILLO DOMINIC J JR ,  CHON YOUNG H

Inventor： MONGILLO DOMINIC J JR ,  CHON YOUNG H ,  KULAK RAYMOND

IPC: F01D9/02 ,  F01D5/08 ,  F01D5/14 ,  F01D5/18 ,  F02C7/18

CPC classification number: F01D5/187 ,  B22C9/10 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/18 ,  F05D2250/311 ,  F05D2250/71 ,  F05D2260/202 ,  F05D2260/22141

Abstract: A component for use in a gas turbine engine is provided. The component has an airfoil portion with a plurality of internal cooling passages and a non-linear trailing edge. The component further has a non-linear array of teardrop shaped assemblies which form a plurality of injection slots for injecting a coolant fluid into a fluid passing over the airfoil portion. The teardrop shaped assemblies are designed to maximize thermal performance of the component by reducing a relative diffusion angle between the injected coolant flow and the streamline direction of the fluid passing over the airfoil portion.

Abstract translation: 提供了用于燃气涡轮发动机的部件。 该部件具有带有多个内部冷却通道和非线性后缘的翼型部分。 该部件还具有泪珠形组件的非线性阵列，其形成多个注入槽，用于将冷却剂流体注入到流过翼型部分的流体中。 泪滴状组件被设计成通过减小喷射的冷却剂流与经过翼型部分的流体的流线方向之间的相对扩散角来使部件的热性能最大化。

公开(公告)号：CA2481351A1

公开(公告)日：2005-05-19

申请号：CA2481351

申请日：2004-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHON YOUNG H ,  MONGILLO DOMINIC J JR

IPC: F01D9/02 ,  F01D5/18 ,  F02C7/18 ,  F01D25/12

Abstract: A turbine engine component, such as a blade or vane, has a system for coolin g a trailing edge portion thereof. The system includes a plurality of rows of pedestals which vary in density along a span of the component. In a preferred embodiment of the present invention, the number of rows of pedestals increases as one moves along the span of the component from an inner diameter region to an outer diameter region.

公开(公告)号：DE602004026814D1

公开(公告)日：2010-06-10

申请号：DE602004026814

申请日：2004-09-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MONGILLO DOMINIC J JR ,  CHON YOUNG H

IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

Abstract: A turbine engine component 10, such as a blade or vane, has a system for cooling a trailing edge portion thereof. The system includes a plurality of rows 24 of pedestals 26 which vary in density along a span of the component 10. In a preferred embodiment of the present invention, the number of rows 24 of pedestals 26 increases as one moves along the span of the component 10 from an inner diameter region 32 to an outer diameter region (30).

公开(公告)号：SG150426A1

公开(公告)日：2009-03-30

申请号：SG2008029324

申请日：2008-04-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CHON YOUNG H ,  MONGILLO DOMINIC J ,  PROPHETER-HINCKLEY TRACY A ,  JOSEPH W BRIDGES JR

Abstract: ANGLED TRIPPED AIRFOIL PEANUT CAVITY A turbine airfoil comprises a wall portion, a cooling channel, an impingement rib, impingement rib nozzles, turbulators and leading edge cooling holes. The wall portion comprises a leading edge, a trailing edge, an outer diameter end, and an inner diameter end. The cooling channel receives cooling air and extends through an interior of the wall portion between the inner diameter end and the outer diameter end. The impingement rib is positioned within the wall portion forward of the cooling channel and between the outer diameter end and the inner diameter end to define a peanut cavity. The impingement rib nozzles extend through the impingement rib for receiving cooling air from the cooling channel. The turbulators are positioned within the peanut cavity to locally influence the flow of the cooling air. The leading edge cooling holes discharge the cooling air from the peanut cavity to an exterior of the wall portion.