公开(公告)号：AU2004200934A1

公开(公告)日：2004-09-30

申请号：AU2004200934

申请日：2004-03-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BONNELL JOHN M ,  BUEY JOHN R

IPC: F02C3/16 ,  F02K1/04 ,  F02K3/10 ,  F23D14/74 ,  F23R3/34 ,  F02C7/32 ,  F02C1/00

Abstract: A turbine engine has a centerbody (38) within a gas flowpath and a downstream tailcone (58) and a pilot (56) at an upstream end of the tailcone (58). A flameholder (82) is positioned in the flowpath outboard of the centerbody (38). The pilot (56) has a first surface (64) diverging in a downstream direction.

公开(公告)号：AT496212T

公开(公告)日：2011-02-15

申请号：AT04252606

申请日：2004-05-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SYNDER TIMOTHY S ,  BUEY JOHN R ,  BRDAR CHRISTOPHER R

IPC: F02K3/00 ,  F02K3/11 ,  F02K3/10 ,  F23D11/12 ,  F23D11/38 ,  F23R3/20 ,  F23R3/28

Abstract: A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

公开(公告)号：AU2004200934B2

公开(公告)日：2006-05-25

申请号：AU2004200934

申请日：2004-03-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BONNELL JOHN M ,  BUEY JOHN R

IPC: F02C3/16 ,  F02K3/10 ,  F02K1/04 ,  F23D14/74 ,  F23R3/34

Abstract: A turbine engine has a centerbody (38) within a gas flowpath and a downstream tailcone (58) and a pilot (56) at an upstream end of the tailcone (58). A flameholder (82) is positioned in the flowpath outboard of the centerbody (38). The pilot (56) has a first surface (64) diverging in a downstream direction.

公开(公告)号：AU2004201436B2

公开(公告)日：2005-09-29

申请号：AU2004201436

申请日：2004-04-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BUEY JOHN R ,  SNYDER TIMOTHY S ,  BRDAR CHRISTOPHER R

IPC: F02K3/00 ,  F02K3/10 ,  F23D11/12 ,  F23R3/20 ,  F23R3/28 ,  F02C007/22 ,  F02K003/10

Abstract: A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

公开(公告)号：NO20041951L

公开(公告)日：2004-11-15

申请号：NO20041951

申请日：2004-05-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BUEY JOHN R ,  SNYDER TIMOTHY S ,  BRDAR CHRISTOPHER R

IPC: F02K3/00 ,  F02K3/10 ,  F23D11/12 ,  F23R3/20 ,  F23R3/28 ,  F02K1/10 ,  F02K1/00 ,  F02K1/30

Abstract: A gas turbine engine augmentor (72) nozzle has an inlet (104) for connection to an augmentor fuel conduit and an outlet (106) for expelling a spray of fuel. A passageway (110) between the inlet (104) and outlet (106) is at least partially bounded by outlet end surface portions (126,128) diverging from each other. The nozzle (70) may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline (150) toward radial.

公开(公告)号：NO20041064L

公开(公告)日：2004-09-14

申请号：NO20041064

申请日：2004-03-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BUEY JOHN R ,  BONELL JOHN M

IPC: F02C3/16 ,  F02K1/04 ,  F02K3/10 ,  F23D14/74 ,  F23R3/34 ,  F02K1/00

Abstract: A turbine engine has a centerbody (38) within a gas flowpath and a downstream tailcone (58) and a pilot (56) at an upstream end of the tailcone (58). A flameholder (82) is positioned in the flowpath outboard of the centerbody (38). The pilot (56) has a first surface (64) diverging in a downstream direction.

公开(公告)号：CA2458280A1

公开(公告)日：2004-09-13

申请号：CA2458280

申请日：2004-02-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BUEY JOHN R ,  BONNELL JOHN M

IPC: F02C3/16 ,  F02K1/04 ,  F02K3/10 ,  F23D14/74 ,  F23R3/34

Abstract: A turbine engine has a centerbody within a gas flowpath and a downstream tailcone and a pilot at an upstream end of the tailcone. A flameholder is positioned in the flowpath outboard of the centerbody. The pilot has a first surface diverging in a downstream direction.