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Luzeng J Zhang

from San Diego, CA
Age ~77
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Also known as:
Luzeng Wang, Zhang Luzeng
Phone and address:
6110 Erlanger St, San Diego, CA 92122
(858) 587-9640
Related to:
Zhimin C Chang, 69Kai Huang, 53Guilian Wang, 54Huiqiu Wang, 54Jia Y Liu, 63Yongzhi Zhang, 54Jin Liu, 56Chih-An Hwang, 68Kehua Zhang, 64Jun Zhang, 56Yue ZhangShutong Wang, 73Wei Chen, 43Lin Cai Jianlin, 62Ruilin Zhang, 61Fred Zhang, 31Hui Wang, 51Shenq N Yang, 69
Connected to:
Aimei Zhang, 45Aining Zhang, 30Aiqing Zhang, 50Alexia Y Zhang, 36Amy X Zhang, 57Angelina Zhang, 54Ashley C Zhang, 60Baomin Zhang, 55Beilei Zhang, 46Carl Zhang, 33

Luzeng Zhang Phones & Addresses

  • 6110 Erlanger St, San Diego, CA 92122 (858) 587-9640 (858) 909-0512
  • Carlsbad, CA
  • College Station, TX
  • La Jolla, CA
  • 6110 Erlanger St, San Diego, CA 92122 (619) 587-9640

Work

Company: Solar turbines May 1993 Position: Senior consulting engineer

Education

Degree: Doctorates, Doctor of Philosophy School / High School: Texas A&M University 1990 to 1993 Specialities: Philosophy, Mechanical Engineering

Skills

Strategic Collaboration

Emails

l***[email protected]

Industries

Oil & Energy

Resumes

Resumes

Luzeng Zhang Photo 1

Senior Consulting Engineer

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Location:
2912 south County Rd, Midland, TX
Industry:
Oil & Energy
Work:
Solar Turbines
Senior Consulting Engineer
Education:
Texas A&M University 1990 - 1993
Doctorates, Doctor of Philosophy, Philosophy, Mechanical Engineering
Skills:
Strategic Collaboration

Publications

Us Patents

Inlet Film Cooling Of Turbine End Wall Of A Gas Turbine Engine

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US Patent:
20090123267, May 14, 2009
Filed:
Oct 24, 2007
Appl. No.:
11/923401
Inventors:
Luzeng John Zhang - San Diego CA, US
Hee Koo Moon - San Diego CA, US
International Classification:
F02C 7/18
US Classification:
415115
Abstract:
The disclosure provides a gas turbine engine having a plurality of nozzle vanes extending between an inner shroud wall and an outer shroud wall of the engine. Each of the vanes includes a leading edge and at least one cooling protrusion extending upstream from a center of the leading edge. A cooling system is provided that is operable to inject cooling air upstream from the vanes. The disclosure also provides a method of cooling a gas turbine engine. The method includes the steps of supplying cooling air to an engine nozzle upstream of a gas directing vane, and adjusting the flow of the cooling air with a cooling protrusion extending forward from a leading edge center of the vane.

Turbine Nozzle

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US Patent:
20130259703, Oct 3, 2013
Filed:
Mar 29, 2012
Appl. No.:
13/433542
Inventors:
Luzeng ZHANG - San Diego CA, US
Juan Yin - San Diego CA, US
Hee Koo Moon - San Diego CA, US
International Classification:
F01D 9/02
US Classification:
416 97 R
Abstract:
A nozzle arrangement for a gas turbine engine comprising a first housing member and a second housing member. The nozzle arrangement may further include a first nozzle and a second nozzle. Each of the first nozzle and second nozzle may extend between the first housing member and the second housing member so as to form a doublet. A plurality of cooling apertures may be arranged on at least one of the first nozzle, the second nozzle, the first housing member, or the second housing member so as to provide a different degree of first order cooling across the doublet.

Turbine Cooling Apparatus

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US Patent:
20130259704, Oct 3, 2013
Filed:
Mar 30, 2012
Appl. No.:
13/436009
Inventors:
Luzeng Zhang - San Diego CA, US
Xubin Gu - San Diego CA, US
Juan Yin - San Diego CA, US
Hee Koo Moon - San Diego CA, US
International Classification:
F01D 5/18
US Classification:
416 97 R
Abstract:
A turbine blade for a gas turbine engine is disclosed. The turbine blade can include at least one internal cooling path, and an internal vane disposed in the at least one internal cooling path. The internal vane can include a central portion, a first leg extending in a first direction from the central portion, and a second leg extending in a second direction from the central portion. The central portion can have a thickness greater than a thickness of the first leg or a thickness of the second leg.

Inlet Film Cooling Of Turbine End Wall Of A Gas Turbine Engine

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US Patent:
20060032233, Feb 16, 2006
Filed:
Aug 10, 2004
Appl. No.:
10/915658
Inventors:
Luzeng Zhang - San Diego CA, US
Hee Moon - San Diego CA, US
International Classification:
F02C 6/08
US Classification:
060782000
Abstract:
The disclosure provides a gas turbine engine having a plurality of nozzle vanes extending between an inner shroud wall and an outer shroud wall of the engine. Each of the vanes includes a leading edge and at least one cooling protrusion extending upstream from a center of the leading edge. A cooling system is provided that is operable to inject cooling air upstream from the vanes. The disclosure also provides a method of cooling a gas turbine engine. The method includes the steps of supplying cooling air to an engine nozzle upstream of a gas directing vane, and adjusting the flow of the cooling air with a cooling protrusion extending forward from a leading edge center of the vane.
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Luzeng J Zhang from San Diego, CA, age ~77 Get Report