Ray M Ramirez

US Patent:

49851420, Jan 15, 1991

Filed:

Dec 15, 1989

Appl. No.:

7/451144

Inventors:

John E. Laycock - San Diego CA
Ray C. Ramirez - San Diego CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

B01D 35147

US Classification:

210130

Abstract:

In order to facilitate release of a filter by-pass valve (10) for filter element replacement in relatively inaccessible locations, the valve (10) includes a housing (12) defining a filter chamber (14) having an inlet (16) communicating with the filter chamber (14) at one end (18) of the housing (12) and an outlet (20) communicating with the filter chamber (14) at the other end (22) of the housing (12). An integral filter-valve assembly (24) is removably positionable within the housing (12) between the inlet (16) and outlet (20). The filter-valve asssembly (24) supports a filter element (26) within the filter chamber (14) in a manner defining a primary flow path from the inlet (16), through the filter element (26), and to the outlet (20). The filter-valve assembly (24) also includes a by-pass valve (28) defining a secondary flow path from the inlet (16) to the outlet (20). A handle (30) integral with the filter-valve assembly (24) extends to a point externally of the housing (12) for removing the filter-valve assembly (24) from the filter chamber (14) to replace the filter element (26).

US Patent:

51136481, May 19, 1992

Filed:

Feb 28, 1990

Appl. No.:

7/486132

Inventors:

Jack R. Shekleton - San Diego CA
Ray C. Ramirez - San Diego CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F02C 705

US Classification:

60 39091

Abstract:

In order to avoid plugging the air passageways (42a) of fuel injectors (42) with carbon particles or lumps in a gas turbine engine (10), the gas turbine engine (10) includes an annular combustor (18) having radial dilution air injection. The gas turbine engine (10) also includes a rotor (12) having turbine blades (14) and a nozzle (16) adjacent the turbine blades (14) which is adapted to direct hot gases of combustion at the turbine blades (14) to cause rotation of the rotor (12). The annular combustor (18) is disposed about the rotor (12) and has an outlet (20) to the nozzle (16), spaced inner and outer walls (22 and 24), and a generally radially extending wall (26) connecting the inner and outer walls (22 and 24). The gas turbine engine (10) further includes a housing (28) substantially surrounding the annular combustor (18) in spaced relation to the inner, outer, and radially extending walls (22, 24 and 26) to define a dilution air flow path (30). The annular combustor (18) has a combustion annulus (36) defined by the inner, outer, and radially extending walls (22, 24 and 26), and a plurality of radially disposed air blast fuel injectors (42).