Christopher D Lyons

US Patent:

20200291858, Sep 17, 2020

Filed:

Feb 24, 2020

Appl. No.:

16/798969

Inventors:

- Farmington CT, US
Christopher B. Lyons - West Hartford CT, US
Nathan Snape - Tolland CT, US

International Classification:

F02C 7/18
F01D 25/14
F01D 5/18
F02C 6/08
F01D 9/06
F02C 3/04
F02C 9/18
F23R 3/28

Abstract:

A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.

US Patent:

20160312615, Oct 27, 2016

Filed:

Dec 18, 2014

Appl. No.:

15/104061

Inventors:

- Hartford CT, US
Christopher B. LYONS - West Hartford CT, US

International Classification:

F01D 5/08
F02C 7/18
F01D 9/06
F01D 25/24
F02C 3/04

Abstract:

A flow system for use in a gas turbine engine includes a diffuser case strut defining a first opening at a first radial end, a second opening at a second radial end, and a strut passage radially therethrough between the first and second openings. A first chamber wall and a second chamber wall define a first mixing chamber disposed radially inward of the diffuser case strut in fluid communication with the strut passage. A third chamber wall extends between the second flowpath wall and the second chamber wall to define a second mixing chamber disposed between the diffuser case strut and the first mixing chamber. The second flowpath wall and the second chamber wall are shaped to form a venturi in the second mixing chamber.

US Patent:

20160215633, Jul 28, 2016

Filed:

Sep 3, 2014

Appl. No.:

14/916291

Inventors:

- Farmington CT, US
Christopher B. Lyons - West Hartford CT, US

International Classification:

F01D 9/04
F23R 3/04
F01D 11/00
F01D 5/18
F01D 25/12

Abstract:

A gas turbine engine includes an engine static structure that has a fluid port. A turbine vane is supported relative to the engine static structure and includes a cooling passage. A flow splitter is provided between the engine static structure and the turbine vane. The flow splitter is configured to divide a flow upstream from the flow splitter into a first fluid flow provided to the fluid port and a second fluid flow provided to the cooling passage.

US Patent:

20160201915, Jul 14, 2016

Filed:

Jun 30, 2014

Appl. No.:

14/911205

Inventors:

- Hartford CT, US
Seth A. Max - Manchester CT, US
Christopher B. Lyons - West Hartford CT, US

International Classification:

F23R 3/12
F23R 3/60

Abstract:

A swirler for a combustor of a gas turbine engine includes a swirler outer body with a male snap component and/or female snap component of a snap-fit interface defined around a swirler central longitudinal axis. A bulkhead assembly for a combustor of a gas turbine engine includes a swirler mounted to a bulkhead support shell through a snap-fit interface.

US Patent:

20160177830, Jun 23, 2016

Filed:

Aug 1, 2014

Appl. No.:

14/910283

Inventors:

- Hartford CT, US
Christopher B. Lyons - West Hartford CT, US
Nathan Snape - Tolland CT, US

International Classification:

F02C 7/18
F02C 9/18
F23R 3/28
F02C 3/04

Abstract:

A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.

US Patent:

20160090914, Mar 31, 2016

Filed:

May 10, 2013

Appl. No.:

14/890188

Inventors:

- Hartford, CT, US
Christopher B. Lyons - West Hartford CT, US

International Classification:

F02C 7/18
F01D 9/02
F02C 7/04
F01D 25/12
F02C 3/06
F01D 5/02
F01D 25/24

Abstract:

An inner diffuser case for a turbine engine includes a fore gas path edge and an aft gas path edge defining a strut, wherein each of the fore gas path edge and the aft gas path edge include a gas path opening, a support cone structure extending radially outward from the strut, wherein the support cone structure is operable to structurally connect the strut to a turbine engine case, a diffuser case skirt structure extending radially inward from the strut, wherein the diffuser case skirt structure is operable to structurally connect the diffuser case strut to an inner support structure of the turbine engine, and at least one direct feed air passage passing radially through the strut including a radially outward upper mixing chamber opening and a radially inward direct air feed opening, the direct air feed opening is connected to a direct air feed.

US Patent:

20150068210, Mar 12, 2015

Filed:

Sep 8, 2014

Appl. No.:

14/479566

Inventors:

- Hartford CT, US
Christopher B. Lyons - West Hartford CT, US

International Classification:

F02C 7/22

US Classification:

60740

Abstract:

A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing.