Nan Jiang

US Patent:

20120316240, Dec 13, 2012

Filed:

Dec 13, 2011

Appl. No.:

13/324750

Inventors:

Shaochun Song - Vista CA, US
Yun Liu - San Diego CA, US
Nan Jiang - Vista CA, US
Lei Yu - Carlsbad CA, US

Assignee:

NITTO DENKO CORPORATION - Osaka

International Classification:

C40B 30/04
A61P 1/16
C12Q 1/02
C12Q 1/68
A61K 31/203

US Classification:

514559, 506 9, 435 612, 435 29

Abstract:

Disclosed herein are methods that generally to the fields of pharmaceutical chemistry, biochemistry, molecular biology and medicine. More particularly, aspects of the invention concern methods to identify a predisposition for fibrosis in a biological sample, methods of identifying agents that modulate the onset of fibrosis, methods of making a formulation that inhibits the onset or progression of fibrosis, and methods of monitoring the progression of fibrosis or the efficacy of a fibrosis treatment.

US Patent:

20200240276, Jul 30, 2020

Filed:

Aug 14, 2017

Appl. No.:

16/638260

Inventors:

- München, DE
Nan Jiang - Charlotte NC, US

International Classification:

F01D 5/20
F01D 5/18

Abstract:

A turbine blade tip includes a squealer tip wall having a forward surface that is continuous with an outer surface of an airfoil pressure sidewall. A plurality of cooling channels are provided spaced apart along a contour of the squealer tip wall. Each cooling channel includes: an inlet configured for receiving a coolant from airfoil internal cavity; an upstream section including a closed channel extending from the inlet to the forward surface of the squealer tip wall; and a downstream section including an open channel formed by a slot on the forward surface of the squealer tip wall. The slot extends radially outward in a downstream direction so as to guide the coolant along the forward surface toward a radially outermost tip of the squealer tip wall.

US Patent:

20200099862, Mar 26, 2020

Filed:

Sep 21, 2018

Appl. No.:

16/138644

Inventors:

- San Diego CA, US
Lei Ma - San Diego CA, US
Fanxing Kong - San Diego CA, US
Nan Jiang - San Diego CA, US

International Classification:

H04N 5/232
G06T 5/00
G06T 7/20
G06T 7/70
G06T 5/50

Abstract:

Aspects of the present disclosure relate to systems and methods for performing multiple frame electronic image stabilization (EIS). An example device may include a memory and a processor configured to receive a current frame for performing multiple frame EIS, determine a location of a cropping in the current frame for an EIS image, and crop current image information from the current frame using the cropping. The cropped current image information is included in the EIS image. The processor further may be configured to determine a portion of the cropping for the EIS image not in the current frame, retrieve from the memory prior image information for the portion of the cropping from one or more prior frames in response to determining the portion of the cropping not in the current frame, and generate, for the current frame, the EIS image including the current image information and the prior image information.

US Patent:

20170087630, Mar 30, 2017

Filed:

Jun 18, 2014

Appl. No.:

15/307073

Inventors:

- Orlando FL, US
Nan Jiang - Charlotte NC, US

International Classification:

B22D 25/02
B22C 9/10
F01D 5/18
B22C 9/04
B22D 29/00
B22C 7/02
B22C 9/24

Abstract:

A method of forming an airfoil (), including: abutting end faces () of cantilevered film hole protrusions () extending from a ceramic core () against an inner surface () of a wax die () to hold the ceramic core in a fixed positional relationship with the wax die; casting an airfoil including a superalloy around the ceramic core; and machining film cooling holes () in the airfoil after the casting step to form an pattern of film cooling holes comprising the film cooling holes formed by the machining step and the cast film cooling holes () formed by the film hole protrusions during the casting step.

US Patent:

20170058678, Mar 2, 2017

Filed:

Aug 31, 2015

Appl. No.:

14/840572

Inventors:

- Orlando FL, US
Nan Jiang - Charlotte NC, US
Jae Y. Um - Winter Garden FL, US
Harry Holloman - Cincinnati OH, US
Steven Koester - Sharonville OH, US

International Classification:

F01D 5/18
F01D 5/14

Abstract:

A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.