公开(公告)号：US09396296B2

公开(公告)日：2016-07-19

申请号：US13592374

申请日：2012-08-23

Applicant: Vikram Singh Mangat ,  Jose-Angel Hernanz Manrique ,  Madhusudana Reddy ,  Punit Tiwari ,  Shreesh Mishra ,  Sunil Kumar ,  Sandhya Jha

Inventor： Vikram Singh Mangat ,  Jose-Angel Hernanz Manrique ,  Madhusudana Reddy ,  Punit Tiwari ,  Shreesh Mishra ,  Sunil Kumar ,  Sandhya Jha

IPC: G06F7/60 ,  G06F17/10 ,  G06F17/50

CPC classification number: G06F17/5018 ,  G06F17/5009 ,  G06F17/5095 ,  G06F2217/16 ,  G06F2217/80

Abstract: A system and method for computing thermal boundary conditions from an unstructured computational fluid dynamics (CFD) simulation for a thermal simulation of a structural component are disclosed. The thermal boundary conditions include convective heat transfer coefficient (HTC) and reference temperature (Tref). In one embodiment, prism cells are formed to capture boundary layer substantially next to a wall of the structural component. Further, tetrahedral cells are formed to capture a diffused temperature layer substantially next to the formed last prism cell and in a direction normal to the wall. Furthermore, temperature of each of the prism cells is computed in the direction normal to the wall until a substantially first tetrahedral cell. In addition, the computed temperature of the prism cell that is substantially adjacent to the first tetrahedral cell is declared as the Tref. Also, the HTC is computed using the obtained Tref.

Abstract translation: 公开了一种用于从结构化计算流体动力学（CFD）模拟计算热边界条件的系统和方法，用于结构部件的热仿真。 热边界条件包括对流传热系数（HTC）和参考温度（Tref）。 在一个实施例中，形成棱镜单元以捕获基本上邻近结构部件的壁的边界层。 此外，形成四面体单元以捕获基本上邻近所形成的最后棱镜单元并且沿垂直于壁的方向的扩散温度层。 此外，每个棱镜单元的温度是在垂直于壁的方向上计算直到基本上第一个四面体单元。 此外，基本上与第一四面体单元相邻的棱镜单元的计算温度被声明为Tref。 此外，使用获得的Tref计算HTC。

公开(公告)号：US20130060541A1

公开(公告)日：2013-03-07

申请号：US13592374

申请日：2012-08-23

Applicant: VIKRAM SINGH MANGAT ,  Jose-Angel Hernanz Manrique ,  Madhusudana Reddy ,  Punit Tiwari ,  Shreesh Mishra ,  Sunil Kumar ,  Sandhya Jha

Inventor： VIKRAM SINGH MANGAT ,  Jose-Angel Hernanz Manrique ,  Madhusudana Reddy ,  Punit Tiwari ,  Shreesh Mishra ,  Sunil Kumar ,  Sandhya Jha

IPC: G06F7/60

CPC classification number: G06F17/5018 ,  G06F17/5009 ,  G06F17/5095 ,  G06F2217/16 ,  G06F2217/80

Abstract: A system and method for computing thermal boundary conditions from an unstructured computational fluid dynamics (CFD) simulation for a thermal simulation of a structural component are disclosed. The thermal boundary conditions include convective heat transfer coefficient (HTC) and reference temperature (Tref). In one embodiment, prism cells are formed to capture boundary layer substantially next to a wall of the structural component. Further, tetrahedral cells are formed to capture a diffused temperature layer substantially next to the formed last prism cell and in a direction normal to the wall. Furthermore, temperature of each of the prism cells is computed in the direction normal to the wall until a substantially first tetrahedral cell. In addition, the computed temperature of the prism cell that is substantially adjacent to the first tetrahedral cell is declared as the Tref. Also, the HTC is computed using the obtained Tref.

Abstract translation: 公开了一种用于从结构化计算流体动力学（CFD）模拟计算热边界条件的系统和方法，用于结构部件的热仿真。 热边界条件包括对流传热系数（HTC）和参考温度（Tref）。 在一个实施例中，形成棱镜单元以捕获基本上邻近结构部件的壁的边界层。 此外，形成四面体单元以捕获基本上邻近所形成的最后棱镜单元并且沿垂直于壁的方向的扩散温度层。 此外，每个棱镜单元的温度是在垂直于壁的方向上计算直到基本上第一个四面体单元。 此外，基本上与第一四面体单元相邻的棱镜单元的计算温度被声明为Tref。 此外，使用获得的Tref计算HTC。

公开(公告)号：US20120298337A1

公开(公告)日：2012-11-29

申请号：US13477080

申请日：2012-05-22

Applicant: Punit Tiwari ,  Shreesh Mishra

Inventor： Punit Tiwari ,  Shreesh Mishra

IPC: F28D15/04 ,  F28F7/00 ,  F28D15/00

CPC classification number: H05K7/2059 ,  B64D2013/0614 ,  F28D15/0266 ,  F28D2021/0021 ,  H05K7/20681

Abstract: A method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by forced and/or natural convection are disclosed. In one embodiment, the apparatus includes a first heat dissipation device to dissipate heat from the aviation electronic equipments housed in an aviation electronic equipment rack using forced convection. Further, the apparatus includes a second heat dissipation device to enhance heat dissipation from the aviation electronic equipments by radiation and natural convection. Furthermore, the second heat dissipation device is strategically disposed with respect to aircraft skin and configured to maximize radiative view factor.

Abstract translation: 公开了一种用于通过强制和/或自然对流冷却的航空电子设备的辐射传热增强的方法和装置。 在一个实施例中，该装置包括第一散热装置，其利用强制对流来散发来自航空电子设备支架的航空电子设备的热量。 此外，该装置包括第二散热装置，以通过辐射和自然对流来增强航空电子设备的散热。 此外，第二散热装置相对于飞行器皮肤策略地设置并且被配置为最大化辐射视图因子。