BackgroundCheck.run
Search For

Linda K Li, 54San Diego, CA

Known as:
Linda E Shabkie Linda Kli Li Linda Lin Da Li
Related to:
Yu Yeung Li 40

Linda Li Phones & Addresses

San Diego, CA   

Spring Valley, CA   

5333 Captains Pl, Agoura Hills, CA 91301    818-9913554    818-9698908   

10 Juniper St, West Hartford, CT 06117    860-5235948   

6600 Yucca, Los Angeles, CA 90028    323-4627709   

1944 Whitley Ave, Los Angeles, CA 90068    323-9698908   

1944 Whitley Ave #205, Los Angeles, CA 90068    323-9698908   

West Hollywood, CA   

10 Juniper Ln, West Hartford, CT 06117    818-9698908   

Work

Position: Personal Care and Service Occupations

Education

Degree: Bachelor's degree or higher
Get Report
Control this profile

Mentions for Linda K Li

Career records & work history

Real Estate Brokers

Linda Li Photo 1

Linda Li

Specialties:
Buyer's Agent, Listing Agent
Work:
kotai Realty
802 E Mission Rd, San Gabriel, CA 91776
626-8076231 (Office)

Medicine Doctors

Linda Li Photo 2

Dr. Linda J Li, Beverly Hills CA - MD (Doctor of Medicine)

Specialties:
Plastic Surgery
Address:
Linda J Li MD
433 N Camden Dr Suite 1190, Beverly Hills, CA 90210
310-2736252 (Phone)
Certifications:
Plastic Surgery, 2002
Awards:
Healthgrades Honor Roll
Languages:
English
Hospitals:
Linda J Li MD
433 N Camden Dr Suite 1190, Beverly Hills, CA 90210
Good Samaritan Hospital
1225 Wilshire Boulevard, Los Angeles, CA 90017
Education:
Medical School
Boston University School of Medicine
Graduated: 1993
Medical School
Usc La
Graduated: 1994
Medical School
Usc La
Graduated: 1998

Linda K. Li

Specialties:
Physical Medicine & Rehabilitation
Work:
Pain Management & Rehabilitation Center
4793 Manhattan Dr, Rockford, IL 61108
815-3987246 (phone) 815-3987276 (fax)
Education:
Medical School
Sun Yat Sen Univ of Med Sci, Guangzhou, China (242 21 Pr 1/71)
Graduated: 1982
Procedures:
Arthrocentesis, Neurological Testing, Physical Therapy, Physical Therapy Evaluation
Conditions:
Abdominal Hernia, Cholelethiasis or Cholecystitis, Overweight and Obesity
Languages:
Chinese, English
Description:
Dr. Li graduated from the Sun Yat Sen Univ of Med Sci, Guangzhou, China (242 21 Pr 1/71) in 1982. She works in Rockford, IL and specializes in Physical Medicine & Rehabilitation.

Linda J. Li

Specialties:
Plastic Surgery
Work:
Linda J Li MD
433 N Camden Dr STE 1190, Beverly Hills, CA 90210
310-2736252 (phone) 310-2736050 (fax)
Education:
Medical School
Boston University School of Medicine
Graduated: 1993
Languages:
Chinese, English, Spanish
Description:
Dr. Li graduated from the Boston University School of Medicine in 1993. She works in Beverly Hills, CA and specializes in Plastic Surgery. Dr. Li is affiliated with Good Samaritan Hospital.
Linda Li Photo 3

Linda T Li

Specialties:
Surgery
Linda Li Photo 4

Linda Jianyuh Li, Beverly Hills CA

Specialties:
Plastic Surgeon
Address:
433 N Camden Dr, Beverly Hills, CA 90210
Board certifications:
American Board of Plastic Surgery Certification in Plastic Surgery

Linda Li resumes & CV records

Resumes

Linda Li Photo 49

Linda Li - Corona, CA

Work:
Quick Check - Pasadena, CA Feb 2006 to Jun 2011
Accountant Payday Express - Los Angeles, CA Oct 1999 to Dec 2005
ER Financial LLC. DBA Bank of China Mar 1995 to Aug 1997
Risk management Bank of China Oct 1990 to Aug 1997
Bank Officer Bank of China Jun 1993 to Feb 1995
Accountant Bank of China Oct 1990 to May 1993
Personal Banker
Education:
California American University - Los Angeles, CA Sep 1997 to Jun 1999
MBA University of International Business and Economics Jan 1993 to Jan 1994
Certificate Zhong Nan University of Finance and Economics Sep 1986 to Jun 1990
BA

Publications & IP owners

Us Patents

Fan Stagger Angle For Geared Gas Turbine Engine

US Patent:
2013034, Dec 26, 2013
Filed:
Feb 10, 2012
Appl. No.:
13/370486
Inventors:
Edward J. Gallagher - West Hartford CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
International Classification:
F02K 3/06
US Classification:
60204, 602261, 416223 A
Abstract:
A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle α with the axis. The stagger angle α is less than 62 at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.

Gas Turbine Engine Airfoil

US Patent:
2019006, Feb 28, 2019
Filed:
Jul 30, 2018
Appl. No.:
16/048981
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F01D 5/14
F01D 5/02
F02C 3/04
F02C 3/14
F01D 15/12
Abstract:
An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0 to 10 in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.

Gas Turbine Engine Airfoil

US Patent:
2018001, Jan 18, 2018
Filed:
Sep 15, 2017
Appl. No.:
15/706025
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F01D 5/14
Abstract:
A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

Gas Turbine Engine Airfoil

US Patent:
2017024, Aug 24, 2017
Filed:
Aug 22, 2014
Appl. No.:
15/113607
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F01D 5/14
F02C 7/36
F02C 3/04
Abstract:
An airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.

Gas Turbine Engine Airfoil

US Patent:
2017018, Jun 29, 2017
Filed:
Mar 16, 2017
Appl. No.:
15/460333
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F04D 29/38
F02K 3/06
F04D 29/32
F02C 3/04
Abstract:
A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0 view. The various views include the 0 view which projects into an axial plane in the axial direction. A 90 view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0 and 90 views. The airfoil has a maximum leading edge projection in a 20 to view. The radial direction is normal to the axial and tangential directions.

Gas Turbine Engine Airfoil

US Patent:
2017013, May 11, 2017
Filed:
Jan 27, 2017
Appl. No.:
15/418115
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F01D 5/14
Abstract:
An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning. The airfoil includes at least one of a least negative dihedral in a range of 5-15% span position, a least negative dihedral in a range of 0-10% span position and a least positive trailing edge dihedral in a 40%-55% span position.

Gas Turbine Engine Airfoil

US Patent:
2017003, Feb 2, 2017
Filed:
Oct 17, 2016
Appl. No.:
15/294939
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F01D 5/14
F02K 3/06
F04D 29/38
F02C 3/107
Abstract:
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is less than 2.0.

Gas Turbine Engine Airfoil

US Patent:
2017002, Jan 26, 2017
Filed:
Aug 25, 2014
Appl. No.:
15/113470
Inventors:
- Farmington CT, US
Byron R. Monzon - Cromwell CT, US
Ling Liu - Glastonbury CT, US
Linda S. Li - Middlefield CT, US
Darryl Whitlow - Middletown CT, US
Barry M. Ford - Middletown CT, US
International Classification:
F04D 29/38
F02K 3/06
F04D 29/32
F02C 3/04
F02C 7/36
Abstract:
In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. Ycorresponds to a tangential distance from a leading edge to the reference point at a given span position. Ycorresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (Y−Y)/(Y−Y) at 40% span position is about 1.5 and (Y−Y)/(Y−Y) at 20% span position is about 2.

Isbn (Books And Publications)

Centre And Provinces: China 1978-1993 Power As Non-Zero-Sum

Author:
Linda Chelan Li
ISBN #:
0198293615

Farm Girls

Author:
Linda Li
ISBN #:
0595328148

Possible Relatives

Cynthia M Li  David Li  Dawei Li  Dayu W Li  De Li  Dean Li  Linda A Johnson  Linda Stander  Linda J Standish 

NOTICE: You may not use BackgroundCheck or the information it provides to make decisions about employment, credit, housing or any other purpose that would require Fair Credit Reporting Act (FCRA) compliance. BackgroundCheck is not a Consumer Reporting Agency (CRA) as defined by the FCRA and does not provide consumer reports.