公开(公告)号：EP2834509A4

公开(公告)日：2015-11-25

申请号：EP13772231

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCKENZIE CRISEN ,  SNYDER TIMOTHY S

IPC: F02K3/00 ,  F02C7/00 ,  F23R3/00 ,  F23R3/16

CPC classification number: F23R3/06 ,  F02C3/04 ,  F05D2220/32 ,  F23R3/007 ,  F23R3/50 ,  F23R2900/03041

Abstract: A combustor includes a shell that at least partially defines a combustion chamber and a grommet mounted in the shell. The grommet has a body that defines a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber. The body carries a first surface, an opposite, second surface and a third surface that defines the passage and joins the first surface and the second surface. The third surface includes a bevel surface with respect to at least one of the first surface and the second surface.

公开(公告)号：DE60336622D1

公开(公告)日：2011-05-19

申请号：DE60336622

申请日：2003-11-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  HOKE JAMES B

IPC: F23R3/28 ,  F23D11/10 ,  F23D11/24 ,  F23R3/04 ,  F23R3/12

公开(公告)号：DE60216168T2

公开(公告)日：2007-10-11

申请号：DE60216168

申请日：2002-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S

IPC: F23R3/06 ,  F23C99/00 ,  F23R3/00 ,  F23R3/10

Abstract: A combustor for a gas turbine engine includes inner and outer liners 32,34 with a row 112, 114 of dilution air holes penetrating through each liner. The row 114 of holes in the outer liner 34 comprise at least a set of large size, major outer holes 116 and may also include a set of smaller size minor outer holes 118 circumferentially intermediate neighboring pairs of the major outer holes 116. The row 112 of holes in the inner liner include dilution air holes circumferentially offset from the major outer holes 116 and may also include a set of minor holes 122 circumferentially intermediate major inner holes 120. The major and minor holes admit respective major and minor jets of dilution air into the combustor. The distribution of major and minor holes and the corresponding major and minor dilution air jets helps to minimize NOx emissions and regulates the spatial temperature profile of the exhaust gases discharged from the combustor.

公开(公告)号：CA2202541C

公开(公告)日：2006-12-19

申请号：CA2202541

申请日：1995-09-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  LOZYNIAK STEVEN A ,  ROSS MICHAEL P ,  MCCOOMB EDWARD J ,  ROSFJORD THOMAS J

IPC: F02C7/232 ,  F23D14/58 ,  F23C7/00 ,  F23C99/00 ,  F23L1/00 ,  F23R3/12 ,  F23R3/28

Abstract: The two scrolls (22) forming air inlet slot (20) are each formed of a fixed vane (36) and a floating vane (38). The thin and hot floating vane (38) is secured to the massive and cooler fixed vane (36) with a longitudinal slidable joint (42). The floating vane may expand without restraint of the fixed vane, so that buckling is avoided and inlet slot (20) is uniform.

公开(公告)号：SG123665A1

公开(公告)日：2006-07-26

申请号：SG200506794

申请日：2005-10-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AGGARWALA ANDREW S ,  GACEK RICHARD E ,  WAGNER JOEL H ,  NOALL JEFF S ,  SNYDER TIMOTHY S

Abstract: An exit guide vane array for a turbine engine includes a set of guide vanes (28) having a solidity and defining fluid flow passages (74) with a chordwisely converging forward portion (80). The high solidity and convergent passage portion (80) resist fluid separation. The vanes (28) may also cooperate with each other to restrict an observer's line of sight to planes (90) upstream of the vane array.

公开(公告)号：CA2523628A1

公开(公告)日：2006-06-21

申请号：CA2523628

申请日：2005-10-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NOALL JEFF S ,  GACEK RICHARD E ,  WAGNER JOEL H ,  AGGARWALA ANDREW S ,  SNYDER TIMOTHY S

IPC: F01D9/02 ,  F01D1/04 ,  F02C7/04 ,  F02C9/16

Abstract: An exit guide vane array for a turbine engine includes a set of guide vanes 28 having a solidity and defining fluid flow passages 74 with a chordwisely converging forward portion 80. The high solidity and convergent passage portion 80 resist fluid separation. The vanes may also cooperate with each other to restrict an observer's line of sight to planes upstream of the vane array.

公开(公告)号：DE69733244D1

公开(公告)日：2005-06-16

申请号：DE69733244

申请日：1997-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

IPC: F02C9/28 ,  F02M61/16 ,  F02C7/232 ,  F23C7/00 ,  F23C7/02 ,  F23C9/00 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34

Abstract: A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combusting a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle assembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane at all operating conditions of the engine.

公开(公告)号：AU2004201436A1

公开(公告)日：2004-12-02

申请号：AU2004201436

申请日：2004-04-06

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02K3/00 ,  F02K3/10 ,  F23D11/12 ,  F23R3/20 ,  F23R3/28 ,  F02C7/22

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：DE69822102D1

公开(公告)日：2004-04-08

申请号：DE69822102

申请日：1998-12-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A ,  MORFORD STEPHEN A ,  VAN DYKE KEVIN J

IPC: F23R3/30 ,  F23C7/00 ,  F23D14/74 ,  F23D14/82 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/34

Abstract: A tangential entry premixing fuel injector (10) for a gas turbine engine combustor includes a pair of offset scrolls (18) whose ends define a pair of entry slots (36) for admitting primary combustion air tangentially into a mixing chamber (28) bounded by the scrolls (18) and by longitudinally spaced endplates (14,16). An array of fuel injection passages (42) extends along the length of the slots. The passage array is configured to inject a primary fuel nonuniformly along the length of the air entry slots and to control the fuel penetration depth d in proportion to slot height H. The injector also includes a flame disgorging centerbody (48) having a bluff tip (54) longitudinally aligned with the injector's discharge plane (22) and a secondary fuel conduit (80) extending through the centerbody for discharging a secondary combustible fluid, preferably gaseous fuel, through a series of fuel discharge openings (84) in the tip (54). The flame disgorging centerbody improves fuel injector durability by resisting ingestion of combustion flame into the mixing chamber (28) and reliably disgorging any flame that is ingested.

公开(公告)号：RU2195575C2

公开(公告)日：2002-12-27

申请号：RU97121008

申请日：1997-12-19

Applicant: TATA DELAWARE ,  UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A

IPC: F02C9/28 ,  F02M61/16 ,  F02C7/232 ,  F23C7/00 ,  F23C7/02 ,  F23C9/00 ,  F23D11/36 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/30 ,  F23R3/34