Air Introduced Within Liner Counter To Flow Of Combustion Products Patents (Class 60/758)
-
Publication number: 20120111014Abstract: A low calorific value fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A nozzle assembly disposed at the closed housing end includes an air blast nozzle and surrounding swirl vanes. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner impingement cools the portion of the liner defining the combustion zone. The combustion liner has an L/D ratio of in the range 1?L/D?4, and a ratio of the combustion zone volume (m3) to heat energy flow rate Q (MJ/sec) in the range 0.0026?V/Q?0.018.Type: ApplicationFiled: November 9, 2010Publication date: May 10, 2012Inventors: Martin Beran, Michal Koranek, Axel Lars-Uno Eugen Axelsson
-
Patent number: 8166764Abstract: A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.Type: GrantFiled: July 21, 2008Date of Patent: May 1, 2012Assignee: United Technologies CorporationInventors: Jaisukhlal V. Chokshi, Craig F. Smith, Carlos G. Figueroa
-
Patent number: 8127526Abstract: A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.Type: GrantFiled: January 16, 2008Date of Patent: March 6, 2012Assignee: United Technologies CorporationInventors: Michael Joseph Murphy, Jeffrey R. Lavin
-
Patent number: 8056342Abstract: A combustor for a turbine engine includes an outer liner having a row of circumferentially distributed outer combustion air holes and an inner liner circumscribed by the outer liner and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners each include at least a major air hole having a first hole size, an intermediate air hole having a second hole size, and a minor air hole having a third hole size. The first, second, and third hole sizes are all different from each other.Type: GrantFiled: June 12, 2008Date of Patent: November 15, 2011Assignee: United Technologies CorporationInventors: Jonathan K. Shelley, Albert K. Cheung, Steven W. Burd, Stuart L. Kozola
-
Patent number: 8051662Abstract: Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative a transition duct assembly for a gas turbine engine includes: an impingement sheet having cooling holes formed therethrough, an inlet end and a non-flanged outlet end, the impingement sheet being operative to be positioned about an exterior of a transition duct such that cooling air is directed to flow about the transition duct; the non-flanged outlet end of the impingement sheet being operative to attach the impingement sheet to the transition duct such that the inlet end is positioned adjacent to an intake end of the transition duct and the outlet end is positioned adjacent to an exhaust end of the transition duct.Type: GrantFiled: February 10, 2009Date of Patent: November 8, 2011Assignee: United Technologies Corp.Inventors: Carlos G. Figueroa, Craig F. Smith
-
Patent number: 8024933Abstract: The invention relates to a wall element for a wall structure of a gas turbine engine combustor. The wall element has an inner, in use, hot surface, and an outer, in use, cooler surface. A plurality of projections is provided on the outer surface to facilitate heat transfer to a coolant flow. The wall element comprises a means to direct more coolant flow at a hot-spot on an adjacent tile than the remainder of the adjacent tile and thereby reducing the thermal gradient across the adjacent tile.Type: GrantFiled: January 8, 2007Date of Patent: September 27, 2011Assignee: Rolls-Royce plcInventors: James R Woolford, Stephen J Mills, Kevin A White
-
Publication number: 20110203287Abstract: A combustor liner for a combustor of a turbine engine includes a single-walled generally cylindrical liner that extends from a head end to an aft end. A venturi is formed on the combustor liner at a location between the head and aft ends. The venturi is formed by first and second straight portions of the combustor liner that angle inward to form a reduced diameter portion. The combustor liner may also include an air deflector to deflect air down onto the exterior of the reduced diameter portion of the single-walled combustor liner. The combustor liner may also include dilution holes, and turbulator rings.Type: ApplicationFiled: February 19, 2010Publication date: August 25, 2011Inventors: Ronald James CHILA, Donald Timothy LEMON
-
Publication number: 20110162373Abstract: A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times the nozzle is in operation. There is no need for a supply of compressed purge air.Type: ApplicationFiled: January 5, 2010Publication date: July 7, 2011Inventors: John INTILE, Predrag POPOVIC, Lucas John STOIA
-
Patent number: 7966822Abstract: A gas turbine combustion system for burning air and fuel into exhaust gases. The gas turbine combustion system may include a combustor, a turbine nozzle integral with the combustor for providing the air to the combustor, and a fuel injector for providing the fuel to the combustor. The turbine nozzle and the fuel injector are positioned within the combustor such that a mixture of the air and the fuel flows in a first direction and the exhaust gases flow in a second direction.Type: GrantFiled: June 30, 2005Date of Patent: June 28, 2011Assignee: General Electric CompanyInventors: Geoffrey David Myers, Thomas Edward Johnson, Stefan Maier, Stanley Kevin Widener
-
Patent number: 7886541Abstract: A combustor wall element arrangement for a gas turbine engine comprises an upstream wall element (50A) overlapping a downstream wall element (50B) and defining a gap (37) and an outlet (35) therebetween. In use, a coolant flow exits the outlet (35) to provide a coolant film (D) across at least a part of the downstream wall element (50B). The outlet (35) has a smaller dimension, normal to the downstream wall element (50B), than the gap (37) thereby increasing the velocity of the coolant flow across at the downstream wall element (50B). The resultant film coolant flow is effective further across the downstream wall element.Type: GrantFiled: January 16, 2007Date of Patent: February 15, 2011Assignee: Rolls-Royce plcInventors: James R Woolford, Stephen J Mills, Kevin A White
-
Publication number: 20110016878Abstract: A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel nozzle.Type: ApplicationFiled: July 24, 2009Publication date: January 27, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: Jonathan Dwight Berry, Geoffrey David Myers
-
Patent number: 7856826Abstract: A method of assembling a combustor for use in a turbine engine is disclosed. The method includes providing a dome assembly ring including a plurality of assembly ring openings, positioning a plurality of elongated rings on the dome assembly ring, providing a cowl assembly including an inner cowl portion and an outer cowl portion that are fabricated from sheet metal, and coupling the inner and outer cowl portions to the dome assembly ring such that each of the plurality of elongated rings is coupled to the dome assembly ring.Type: GrantFiled: November 10, 2006Date of Patent: December 28, 2010Assignee: General Electric CompanyInventors: Daniel Dale Brown, Michael Terry Bucaro, Jeff Martini
-
Publication number: 20100257864Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.Type: ApplicationFiled: April 9, 2009Publication date: October 14, 2010Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Aleksander Kojovic, David C. Jarmon, Jun Shi, Shaoluo L. Butler
-
Publication number: 20100257869Abstract: The invention relates to a gas turbine, comprising an annular combustion chamber and an upstream diffuser, with a throughflow essentially parallel to a turbine longitudinal axis, at a distance from said axis at least partly less than the annular combustion chamber, in which a compressed gas may be divided into several partial flows at a branching point, whereby at least one of the partial flows is a cooling gas flow. A main deflection region is provided in said diffuser, directed at an angle to the turbine longitudinal axis towards the annular combustion chamber.Type: ApplicationFiled: July 16, 2004Publication date: October 14, 2010Inventors: Christian Cornelius, Reinhard Mönig, Peter Tiemann, Iris Oltmanns
-
Patent number: 7770397Abstract: A gas turbine engine combustor having a dome heat shield includes a cooling scheme having a plurality of impingement cooling holes extending through the combustor and a plurality of adjacent ejector holes for directing cooling air past the heat shield lips of the dome heat shields. The impingement and ejector holes are preferably staggered to reduce interaction therebetween.Type: GrantFiled: November 3, 2006Date of Patent: August 10, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Lorin Markarian, Kenneth Parkman, Stephen Phillips
-
Patent number: 7757492Abstract: A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.Type: GrantFiled: May 18, 2007Date of Patent: July 20, 2010Assignee: General Electric CompanyInventors: John Charles Intile, Madhavan Poyyapakkam, Ganesh Pejawar Rao, Karthick Kaleeswaran
-
Publication number: 20100115966Abstract: In a gas turbine combustor, a cavity (49) with which a plurality of first air passages (66) communicates is formed by covering with a cover (62) a concave portion (65) of a top hat main body (61) in which the first air passages (66) are formed along the circumferential direction of the top hat main body (61), a plurality of second fuel passages (67) that communicates with the first fuel passages are formed by connecting an inner ring (63) and an outer ring (64) to the top hat main body (61) and by connecting the inner ring (63) and the outer ring (64) to each other, a peg (52) is fixed on the inner ring (63) to communicate with the second fuel passage (67) through a third air passage (68), and thin wall portions (63b, 64b) that serve as a thermal elongation absorbing unit by which thermal elongation is absorbed are provided on the inner ring (63) and the outer ring (64).Type: ApplicationFiled: April 11, 2008Publication date: May 13, 2010Applicant: MITSUBISHI HEAVY INDUSTRIES, LTDInventors: Tomoto Nagai, Eigo Katou, Tetsu Konishi
-
Patent number: 7712314Abstract: A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines a passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the venturi passageway. The venturi passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the passageway for cooling the venturi.Type: GrantFiled: January 21, 2009Date of Patent: May 11, 2010Assignee: Gas Turbine Efficiency Sweden ABInventors: John Barnes, Adam Bailey, John Battaglioli, Robert Bland
-
Patent number: 7707836Abstract: A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines an internal passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the internal passageway. The internal passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the internal passageway for cooling the venturi.Type: GrantFiled: August 6, 2009Date of Patent: May 4, 2010Assignee: Gas Turbine Efficiency Sweden ABInventors: John Barnes, Adam Bailey, John Battaglioli, Robert Bland
-
Patent number: 7707835Abstract: A combustor has a flow sleeve and a flow liner defining a generally axial flow direction of compressor discharge air toward combustor burners. A casing is secured to the forward end of the flow sleeve defining an annular plenum along the interior of the flow sleeve. Openings through the flow sleeve supply compressor discharge air into the plenum where the air changes direction for flow through apertures into and generally coaxially with the free air stream. The axial injection minimizes or eliminates energy losses due to cross flow injection within the axial air stream while continuing to cool the liner.Type: GrantFiled: June 15, 2005Date of Patent: May 4, 2010Assignee: General Electric CompanyInventors: John Joseph Lipinski, Thomas Edward Johnson, Robert Paul Ziegler, Mark Stewart Schroder
-
Publication number: 20090145099Abstract: Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.Type: ApplicationFiled: December 6, 2007Publication date: June 11, 2009Applicant: POWER SYSTEMS MFG., LLCInventors: Stephen Jennings, Peter Stuttaford, Stephen W. Jorgensen
-
Patent number: 7194866Abstract: A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an exhaust pipe with relatively uncomplicated assembly interfaces. The static structure defines airflow and lubrication passages which communicate lubricant and airflow to each shaft bearing such that an adequate measured quantity of lubricant is supplied to the bearings in response to engine speed. The airflow through the airflow passage carries the lubrication supplied to the forward bearing toward the aft bearing to further lubricate the aft hot section bearing.Type: GrantFiled: June 20, 2003Date of Patent: March 27, 2007Assignee: Hamilton Sundstrand CorporationInventors: Anthony Jones, Mark Harris, Eric Alexander, Patrick Lydon
-
Patent number: 6968693Abstract: A low emission turbine includes a reverse flow can-type combustor that generally includes a primary and secondary fuel delivery system that can be independently controlled to produce low CO, UHC, and NOx emissions at design set point and at conditions other than design set point. The reverse flow can-type combustor generally includes an annularly arranged array of swirler and mixer assemblies within the combustor, wherein each swirler and mixer in the array includes a primary and secondary fuel delivery system that can be independently controlled. Also disclosed herein is a can-type combustor that includes fluid passageways that perpendicularly impinge the outer surface of a heat shield. Processes for operating the can-type combustors are also disclosed.Type: GrantFiled: September 22, 2003Date of Patent: November 29, 2005Assignee: General Electric CompanyInventors: Andrei Colibaba-Evulet, Michael John Bowman, Simon Ralph Sanderson, Anthony John Dean
-
Patent number: 6837053Abstract: In order to provide a method of air guidance and a design for a gas turbine combustion chamber which permits improved cooling and reduced pressure losses and which avoids the overcooling phenomena by specific reaction to hot spots, a gas turbine combustion chamber includes a casing and at least one hollow element. The at least one hollow element is in connection with air guidance regions of the combustion chamber via at least two openings. As such, a tangential through-flow exists with a subsequent axial flow to the burner.Type: GrantFiled: June 20, 2002Date of Patent: January 4, 2005Assignee: Siemens AktiengesellschaftInventor: Peter Tiemann
-
Patent number: 6286317Abstract: A liner for a gas turbine engine combustor, including an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget joining the upstream and downstream liner sections for providing mechanical stiffness at a junction of the upstream and downstream liner sections. The cooling nugget further includes a first portion connected to the upstream liner section, a second portion connected to the downstream liner section, and a third portion joining the first and second cooling nugget portions at a first end, the third cooling nugget portion extending radially from the first end, wherein the cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section.Type: GrantFiled: December 18, 1998Date of Patent: September 11, 2001Assignee: General Electric CompanyInventors: David L. Burrus, Arthur W. Johnson, George E. Moertle
-
Patent number: 6193502Abstract: The fuel is fed centrally into a fire tube (3), where it is mixed with combustion air in a combustion zone. The air exits through first and second air line nozzles (4 or 5) which are arranged in two directly adjoining rows (6, 7) and inclined in the direction of counterflow at an angle of 60° to the axis of the fire tube. The distance (x) between the fuel nozzle (9) and the openings of the first air line nozzles (4) is 0.70 times the diameter of the fire tube. In addition, the second air line nozzles (5) extend into the fire tube by a distance (y) which is 0.17 times the diameter of the fire tube. The total cross-section of the second air line nozzles (5) is 0.6 times that of the first air line nozzles (4). A highly turbulent toroidal eddy forms inside the fire tube (3) which generates a very homogeneous mixture across the cross-section of said fire tube (3). This results in lower NOx values and even temperature distribution already inside the fire tube.Type: GrantFiled: November 22, 1999Date of Patent: February 27, 2001Assignee: Ruhrgas AktiengesellschaftInventors: Anatolij Vladimirovic Sudarev, Jevgenij Dimitrijevic Vinogradov, Jurij Ivanovic Zacharov, Stanislav Vesely, Gustav Poslusny, Karl Peters, Karl-Heinz Scholz, Erik Zizow
-
Patent number: 6029455Abstract: A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The combustion chamber also has at least two rows of insulating tiles arrayed on the casing in forward and rear rows with both rows extending circumferentially around the inner surface of the casing bounding the combustion chamber. Each rear tile has a forward edge portion with a sloping wall and each forward tile has a tapered rear edge portion overlapping the forward edge portion with a clearance therebetween such that the tampered rear edge portion and the sloping wall bound a slot opening into the combustion chamber and slanting towards the rear of the combustion chamber to facilitate the formation of an air cooling film on inner surfaces of the tiles.Type: GrantFiled: August 28, 1997Date of Patent: February 29, 2000Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation S.N.E.C.M.A.Inventor: Denis Sandelis
-
Patent number: 6018950Abstract: A modular cooling panel for cooling a turbine member is provided. The cooling panel comprises a first panel having a relative width, relative length, upper surface and lower surface. The upper surface defines at least one corrugated portion traversing along a portion of the relative width of the upper surface. The corrugated portion defines a cooling flow channel through which a cooling fluid can travel to cool the turbine member. The cooling flow channel has at least one inlet opening for enabling the cooling fluid to enter into the cooling flow channel. The lower portion surface of the first panel is adapted to be coupled in fluid communication with the turbine member.Type: GrantFiled: June 13, 1997Date of Patent: February 1, 2000Assignee: Siemens Westinghouse Power CorporationInventor: Scott Michael Moeller
-
Patent number: 5826431Abstract: Provided are a gas turbine multi-hole film-cooled combustor liner, which can be manufactured with improved accuracy in shape and position of cooling holes in a very short time, ensuring desirable buckling strength and satisfactory cooling performance. A planar flat member is curved to form a liner shell of a cylindrical shape, the cylindrical member is welded in the longitudinal direction thereof to form a cylindrical shell. Then a wavy configuration and a corrugated configuration are formed on the cylindrical shell by a hydro-bulging method, cooling holes are formed through the liner shell by laser drilling at or near wave crest portions of the wavy configuration of the liner shell, and inner rings are attached to the liner shell by resistance spot welding or vacuum brazing.Type: GrantFiled: February 5, 1996Date of Patent: October 27, 1998Assignee: Kabushiki Kaisha ToshibaInventors: Yoshinobu Makino, Kiyoshi Yamada, Hiroshi Matsui, Yoshihiro Aburatani, Yamato Kaminaka, Hiroshi Kubo, Hiroaki Okamoto
-
Patent number: 5727378Abstract: This invention pertains to small air breathing gas turbine engines (1). Engines of the invention employ improved combustion systems, including improved fuel injection systems and improved combustor design. These improvements enable the engine to idle at speeds as low as one-tenth the maximum operating speed of the engine, which gives the engine an increased range of operating speeds. The improved designs generally provide for pre-mix assemblies intimate with the fuel injectors, a typically flame-free primary "A" mixing zone in the combustion chamber, and a primary "B" combustion zone, in addition to the secondary combustion zone and the dilution zone. In preferred embodiments, the bearing assembly is located between the compressor and the turbine wheel. A cooling cavity is provided between the turbine wheel and the bearing assembly, thus protecting the bearings from the turbine heat.Type: GrantFiled: August 25, 1995Date of Patent: March 17, 1998Assignee: Great Lakes Helicopters Inc.Inventor: Jeffrey L. Seymour
-
Patent number: 5331803Abstract: Undesirable high temperature gradients associated with inadequate mixing of dilution air with gases of combustion in turbines is avoided in a structure wherein dilution air is injected with a high degree of circumferential swirl through an opening (50) to the interior of an annular combustor (20) at the outlet (36) thereof which is connected to a turbine nozzle (46). The high circumferential swirl generates high "g" forces causing rapid penetration of the dilution air in the radial direction through the combustion air stream and the length of the path of the combined stream, and thus residence time and thoroughness of mixing, can be controlled through the use of a baffle (60) overlying the opening (50) to direct the dilution air countercurrently to the gases of combustion prior to introduction into the stream thereof.Type: GrantFiled: July 24, 1989Date of Patent: July 26, 1994Assignee: Sundstrand CorporationInventor: Jack R. Shekleton
-
Patent number: 4926630Abstract: Warping of the rear turbine shroud 54 and the resulting cracking of turbine nozzle vanes 24 may be eliminated in a radial inflow turbine having an annular combustor 30 with a radially outer wall 32 opening on a compressed air plenum 48 by locating a plurality of tubes 70 on the radially outer wall 32 in fluid communication with the plenum 48 and extending the tubes 70 inwardly so that the radially inner ends 76 are adjacent the radially outer edge 56 of the turbine shroud 54. The tubes 70 thus direct sweeping streams of cooling air along the rear turbine shroud 54 to cool the same and prevent warpage.Type: GrantFiled: December 12, 1988Date of Patent: May 22, 1990Assignee: Sundstrand CorporationInventor: Jack R. Shekleton
-
Patent number: 4765146Abstract: The combustion chamber is characterized by an annular-cylindrical space, which consists of two reaction chambers (8), arranged at the end, and a collision chamber (12) placed therebetween. The reaction chambers (8) are fitted at their face-sided ends with a number of burner elements (A, B), arranged axially parallel, their number depending on the output of the combustion chamber, which burner elements are in each case mirror-symmetrical to each other in relation to the central axis of the collision chamber (12). From the collision chamber (12), an annular mixing chamber (15) goes off to the turbine inlet (17). Each burner element (A, B) is provided with a twist member (6, 11), which in each case is orientated in opposed sense of rotation compared with the mirror-symmetrically arranged twist member.Type: GrantFiled: July 27, 1987Date of Patent: August 23, 1988Assignee: BBC Brown, Boveri & Company, Ltd.Inventors: Jaan Hellat, Jakob Keller
-
Patent number: 4719748Abstract: A transition duct in an advanced heavy duty gas turbine engine is cooled by impingement jets formed by apertures in a sleeve spaced a distance from the surface to be cooled. The sleeve is configured so as to duct spent impingement air towards the combustor, where it can be subsequently used for mixing with, and combustion of, the fuel, or for cooling of the combustor. The distance between the impingement sleeve and the transition duct surface is varied to control the velocity of air crossflow from spent impingement air in order to minimize the pressure loss due to crossflow. The cross-sectional areas of the apertures are varied to project impingement jets over the various distances and crossflow velocities. Generally, larger aperture areas are used with larger distances.Type: GrantFiled: December 15, 1986Date of Patent: January 19, 1988Assignee: General Electric CompanyInventors: Lewis B. Davis, Jr., Walter W. Goodwin, Charles E. Steber
-
Patent number: 4676736Abstract: A combustion device for combustion of a gaseous fuel with air is provided with means for supplying gas automatically at a mass flow rate corresponding to a mass flow of air governed by the demand of heat. The gas is supplied at a pressure slightly above atmospheric pressure to an ejector using preheated primary air as a carrying medium. The ejector is mounted in a flow path in series with and after a blower, a recuperative preheater and a swirl device but prior to a system of heater tubes and the exhaust passages of the preheater.Type: GrantFiled: October 18, 1985Date of Patent: June 30, 1987Assignee: Gas Research InstituteInventor: Jan .ANG.. Alpqvist
-
Patent number: 4642993Abstract: A combustor liner wall is provided with an interior wall, an exterior wall and a honeycomb structure disposed therebetween. The honeycomb structure is formed with generally radially aligned cells. The cells are constructed to define alternate array of gaps between the honeycomb structure and the interior and exterior walls, respectively. The cooling air thus undergoes repeated undulations and mixing as it flows through the liner wall.Type: GrantFiled: April 29, 1985Date of Patent: February 17, 1987Assignee: Avco CorporationInventor: Ervin J. Sweet
-
Patent number: 4628687Abstract: A combustor for a gas turbine including a burner defining an axial fluid flow path between upstream and downstream ends, a burner casing coaxially surrounding the burner and defining an annular conduit for inlet gas flow from downstream to upstream ends of the burner, ports for introducing part of the inlet gas into the upstream end of the burner, a fuel nozzle introducing fuel into the upstream end of the burner, slots circumferentially disposed around the burner casing upstream of the ports and a conduit and valve arrangement for introducing external air to the annular conduit through the slots to generate an annular vortex to restrict inlet gas flow to the ports when the turbine is operating at predetermined operating conditions.Type: GrantFiled: May 15, 1984Date of Patent: December 16, 1986Assignee: A/S Kongsberg VapenfabrikkInventor: Sigmunn Strom
-
Patent number: 4475344Abstract: An improved combustor basket for a land-based combustion turbine comprises a plurality of ring segments joined in telescoping fashion to form a constant diameter basket, the downstream end of each ring segment having an extended lip for improved film cooling of the interior surface of the ring segments, a combustor dome adjoining the upstream end of the combustor basket and having an interior splash plate directing a cooling air film along the interior surface of the dome wall, fuel injecting means, and oval-shaped scoops for directing the flow of compressed air into the combustion zone. Each ring segment, excluding the first, comprises an upstream cylindrical section, a conical section, and a downstream cylindrical section, which geometrical arrangement permits construction of a constant diameter combustor basket. The combined improvements of the present combustor basket result in more efficient and complete combustion, which results in the production of less smoke.Type: GrantFiled: February 16, 1982Date of Patent: October 9, 1984Assignee: Westinghouse Electric Corp.Inventors: Stephen E. Mumford, Edward W. Tobery
-
Patent number: 4446693Abstract: A cooled wall structure for a gas turbine engine comprises a perforated and an inner wall in which the walls are capable of relative movement to cope with the thermal strains experienced by the combustion chamber during operation of the engine. The inner wall comprises a number of wall elements attached to the outer wall in the manner of overlapping tiles. Each wall element is immovably secured to the outer wall at the mid-point of its downstream end and the sides of each wall element are movably attached to the outer wall adjacent the sides of the downstream end of the wall element.The upstream end of each wall element is located between the outer wall and an adjacent flow in either an upstream or a downstream direction between the walls.The wall elements can have a plurality of raised lands to increase the surface area of the elements and to protect the incoming cooling air against the cross-flow of cooling air already flowing in the wall structure.Type: GrantFiled: October 20, 1981Date of Patent: May 8, 1984Assignee: Rolls-Royce LimitedInventors: Anthony Pidcock, George Pask
-
Patent number: 4365951Abstract: A combustion device of the type in which fuel is supplied in liquid phase through a "walking-stick" is improved by imparting a rotary movement to the air passing the "walking-stick". The fuel will form a film which is volatired and mixed so thoroughly with air that the temperature at the end of the "walking-stick" may be used as an indication of the prevailing proportion between the mass flows of supplied air and fuel.Type: GrantFiled: June 13, 1980Date of Patent: December 28, 1982Inventor: Jan Alpkvist
-
Patent number: 4339925Abstract: A method and apparatus for cooling the hot gas casing of a gas turbine power plant is disclosed. The apparatus includes a shell which is spaced from but which encompasses the hot gas casing so as to form an air channel about the casing. A compressor provides a supply of cooling air which flows into the air channel through openings in the shell, and which air absorbs heat from the hot gas casing as it flows through the air channel.Type: GrantFiled: July 9, 1979Date of Patent: July 20, 1982Assignee: BBC Brown, Boveri & Company LimitedInventors: Jean Eggmann, Hans Graf, Tadeusz Zaba
-
Patent number: 4301657Abstract: A gas turbine combustion chamber in which the primary air inlets in a peripheral wall of the combustion chamber are defined by open-ended tubes extending inwardly from the peripheral wall by a substantial distance into the combustion chamber and having their inner, that is their outlet, ends facing in an upstream direction within the combustion chamber, whereby each of the tubes will introduce a stream of air with at least a component of motion in the upstream direction along or parallel with the longitudinal axis of the combustion chamber, thereby to effect recirculation of fuel, air and combustion gases within the combustion chamber. Similar air inlet tubes may be provided for introducing secondary and tertiary air into the combustion chamber.Type: GrantFiled: May 3, 1979Date of Patent: November 24, 1981Assignee: Caterpillar Tractor Co.Inventor: Robert N. Penny
-
Patent number: 4244179Abstract: An annular combustion chamber which has structural elements for delivery of primary air to sustain and stabilize burning and elements for admission of secondary air into the dilution zone. The primary air delivery elements intended for stabilization of burning are made so that at least two curved slotted passages are formed for tangential admission of the air into the combustion zone. The passage wall plates are concentric, being arranged so that the outer wall plate of each preceding passage is naturally the inner wall plate of the subsequent one displaced relative to the former in the downstream direction. The slotted passages have a substantially constant flow-passage along the entire annular combustion chamber periphery (length).Type: GrantFiled: November 9, 1978Date of Patent: January 13, 1981Inventors: Gennady P. Kainov, Vladimir G. Kuznetsov, Anatoly M. Polyakov, Igor A. Shleenkov
-
Patent number: 4211073Abstract: This invention concerns an improved combustion chamber comprising two concentric sheet metal cases forming a space into which air is admitted. The air passes from the space to the interior of the chamber in primary, secondary, annular, and tertiary air flows. The fuel coming from lateral nozzles forms a flame which is directed at first toward the closed end, then turned back by the secondary air flow. The external case comprises two walls between which a cooling flow circulates. The invention thereby achieves reduction in atmospheric pollution from exhaust gases.Type: GrantFiled: February 27, 1978Date of Patent: July 8, 1980Assignee: GuidasInventor: Jack Guillot