Patents by Inventor Desmond Close
Desmond Close has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 7181914Abstract: A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member 46 which forces air flowing through the pre-diffuser 40 to separate, initially to be directed away from the midline 48 before subsequently being allowed to diffuse back towards the midline 48. The majority of the diffusion takes place on the walls of the central member and is thus in an inner region of the annulus of air ejected from the pre-diffuser to pass to the combustor. Any boundary losses therefore do not significantly effect air at the extremities of this annulus, this air being destined for the annuli of the combustor and requiring relatively high energy levels.Type: GrantFiled: June 25, 2003Date of Patent: February 27, 2007Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close
-
Patent number: 7089742Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.Type: GrantFiled: August 7, 2003Date of Patent: August 15, 2006Assignee: Rolls-Royce plcInventors: Michael P. Spooner, Anthony Pidcock, Desmond Close
-
Patent number: 7080516Abstract: A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (38) and a downstream region (40). Distribution means (41) is arranged between the downstream region (40) and the outlet (28) to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region (40) to the cross-sectional area of the upstream region (38) is greater than 1.5 to 1.Type: GrantFiled: December 23, 2003Date of Patent: July 25, 2006Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close
-
Publication number: 20060117755Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.Type: ApplicationFiled: August 7, 2003Publication date: June 8, 2006Inventors: Michael Spooner, Anthony Pidcock, Desmond Close
-
Patent number: 7000397Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: GrantFiled: December 27, 2004Date of Patent: February 21, 2006Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close, Michael P Spooner
-
Publication number: 20050262846Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: ApplicationFiled: December 27, 2004Publication date: December 1, 2005Inventors: Anthony Pidcock, Desmond Close, Michael Spooner
-
Patent number: 6857275Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: GrantFiled: October 21, 2003Date of Patent: February 22, 2005Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close, Michael P. Spooner
-
Publication number: 20050034399Abstract: A double wall structure (22) for a combustor (15) of a gas turbine engine (10) comprising an inner wall (28) and an outer wall (27), the inner wall (28) comprising a plurality of main tiles (50), the main tiles (50) are secured to the outer wall (27) by a securing means (35), wherein the inner wall (28) further comprises a plurality of edge tiles (52) which are secured to the outer wall (27) by securing means (35), each edge tile (52) overlapping at least one edge (30, 31, 54, 61) of a main tile (50) thereby further securing the main tiles (50) to the outer wall (27).Type: ApplicationFiled: July 1, 2004Publication date: February 17, 2005Inventors: Anthony Pidcock, Desmond Close
-
Publication number: 20040195396Abstract: A gas diffusion arrangement (22) for a gas turbine engine (10) is disclosed. The gas diffusion arrangement (22) has an inlet (26) and an outlet (28) for the gas, and comprises diffusion means (32) having an upstream region (38) and a downstream region (40). Distribution means (41) is arranged between the downstream region (40) and the outlet (28) to distribute the gas into a desired flow pattern. The area ratio of the cross-sectional area of the downstream region (40) to the cross-sectional area of the upstream region (38) is greater than 1.5 to 1.Type: ApplicationFiled: December 23, 2003Publication date: October 7, 2004Inventors: Anthony Pidcock, Desmond Close
-
Publication number: 20040083739Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: ApplicationFiled: October 21, 2003Publication date: May 6, 2004Applicant: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close, Michael P. Spooner
-
Patent number: 6708499Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: GrantFiled: February 22, 2002Date of Patent: March 23, 2004Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close, Michael P Spooner
-
Publication number: 20040045298Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: ApplicationFiled: September 10, 2003Publication date: March 11, 2004Applicant: ROLLS-ROYCE PLCInventors: Anthony Pidcock, Desmond Close, Michael P. Spooner
-
Publication number: 20040011043Abstract: A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member 46 which forces air flowing through the pre-diffuser 40 to separate, initially to be directed away from the midline 48 before subsequently being allowed to diffuse back towards the midline 48. The majority of the diffusion takes place on the walls of the central member and is thus in an inner region of the annulus of air ejected from the pre-diffuser to pass to the combustor. Any boundary losses therefore do not significantly effect air at the extremities of this annulus, this air being destined for the annuli of the combustor and requiring relatively high energy levels.Type: ApplicationFiled: June 25, 2003Publication date: January 22, 2004Inventors: Anthony Pidcock, Desmond Close
-
Patent number: 6666025Abstract: A wall element (29) for a wall structure (21) of a gas turbine engine combustor (15). The wall element (29) comprises a main member (36) with an upstream edge region (30) and a downstream edge region (31). A plurality of heat removal members (38) are provided on the main member (36). The downstream edge (35) of the wall element and/or the downstream facing surface of the heat removal members closest to the downstream edge (35) are provided with a thermally resistant coating.Type: GrantFiled: February 16, 2001Date of Patent: December 23, 2003Assignee: Rolls-Royce plcInventors: Michael P Spooner, Anthony Pidcock, Desmond Close
-
Publication number: 20030145604Abstract: A double wall structure (22) for a combustor (15) of a gas turbine engine (10) comprising an inner wall (28) and an outer wall (27), the inner wall (28) comprising a plurality of main tiles (50), the main tiles (50) are secured to the outer wall (27) by a securing means (35), wherein the inner wall (28) further comprises a plurality of edge tiles (52) which are secured to the outer wall (27) by securing means (35), each edge tile (52) overlapping at least one edge (30, 31, 54, 61) of a main tile (50) thereby further securing the main tiles (50) to the outer wall (27).Type: ApplicationFiled: December 30, 2002Publication date: August 7, 2003Inventors: Anthony Pidcock, Desmond Close
-
Patent number: 6470685Abstract: A wall structure for a gas turbine combustor arranged to have a general direction of fluid flow therethrough includes inner and outer walls defining a space therebetween. The inner wall is made up of a plurality of tiles having axial edges aligned generally with the direction of fluid flow, a gap being defined between axial edges of adjacent tiles. Orifices are provided within the axial edges to direct leakage air passing through the gaps to give the leakage air a flow component in the general direction of fluid flow through the combustor.Type: GrantFiled: April 6, 2001Date of Patent: October 29, 2002Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close, Michael P Spooner
-
Publication number: 20020124572Abstract: A wall element for use as part of an inner wall of a gas turbine engine combustor wall structure is of cast construction and includes a plurality of cooling apertures provided therethrough and formed during the casting process. The cooling apertures may be located in positions where they could not be conventionally formed by laser drilling.Type: ApplicationFiled: February 22, 2002Publication date: September 12, 2002Inventors: Anthony Pidcock, Desmond Close, Michael P. Spooner
-
Patent number: 6408628Abstract: A wall element (29A, 29B) for a combustor (20) of a gas turbine engine (10). The wall element (29A, 29B) defines an axis. In use, the axis is arranged generally parallel to the principal axis of the engine (10). In one aspect, the length of the wall element (29B) along the axis is at least substantially 20% of the length of the wall element (29B) transverse to the axis. In another aspect, the wall element (29A, 29B) has a first pair of opposite edges extending transverse to the axis and a second pair of opposite edges (48, 50) extending transverse to the first pair, at least one of the second pair of edges (48, 50) being angled relative to the axis of the wall element (29A, 29B).Type: GrantFiled: November 2, 2000Date of Patent: June 25, 2002Assignee: Rolls-Royce plcInventors: Anthony Pidcock, Desmond Close, Michael P. Spooner
-
Patent number: 6334297Abstract: A combustor arrangement (8) for a gas turbine engine (3) comprising a combustion chamber, fuel nozzles(52a,52b), and a bled diffuser (7) located upstream of said combustion chamber to, in use, direct an airflow from an upstream compressor (6) into the combustor (8). The fuel nozzles (52a,52b) arranged in use to supply fuel into the combustion chamber where it is mixed and combusted with the airflow from the compressor (6). The bled diffuser (7) adapted to bleed off a portion of said airflow from a main airflow into the combustion chamber. At least one bleed duct (46) is connected to the bled diffuser (7) to return and direct the air bled from the diffuser (7) to a main gas flow through the engine (3) at a location downstream of the fuel supply means (52a,52b). The bled air from the diffuser (7) preferably providing cooling of a part of the gas turbine engine (3), for example part of the turbine (10) or combustor outlet vane (58), downstream of the combustor (8).Type: GrantFiled: July 24, 2000Date of Patent: January 1, 2002Assignee: Rolls-Royce plcInventors: Geoffrey M Dailey, Anthony Pidcock, Desmond Close
-
Patent number: 6324830Abstract: A fuel injector assembly designed to withstand a predetermined impact load resulting from ingestion of a bird or other foreign object into the combustion stage of a gas turbine engine comprises a body member adapted to be mounted adjacent to and to extend into the combustion chamber and an abutment member disposed downstream of the injector assembly in the direction of air flow through the combustion stage, the arrangement being such that the body member moves into contact with the abutment member when subjected to an impact load in excess of the impact load it is designed to withstand.Type: GrantFiled: September 29, 2000Date of Patent: December 4, 2001Assignee: Rolls-Royce plcInventors: Michael P Spooner, Anthony Pidcock, Desmond Close