EP0578048B1 - Cylindrical combustion chamber for gas turbine - Google Patents
Cylindrical combustion chamber for gas turbine Download PDFInfo
- Publication number
- EP0578048B1 EP0578048B1 EP93109972A EP93109972A EP0578048B1 EP 0578048 B1 EP0578048 B1 EP 0578048B1 EP 93109972 A EP93109972 A EP 93109972A EP 93109972 A EP93109972 A EP 93109972A EP 0578048 B1 EP0578048 B1 EP 0578048B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- gas turbine
- perforated cone
- chamber casing
- cone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/54—Reverse-flow combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/231—Three-dimensional prismatic cylindrical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Definitions
- the invention relates to a cylindrical combustion chamber housing of a gas turbine with an unbladed inlet manifold with a narrowing annular channel arranged around the combustion chamber housing for introducing compressor air through openings into the interior of a combustion chamber.
- a cylindrical combustion chamber housing of a gas turbine is known from document FR-A-2 439 362.
- the compressor air flows from an unshielded rectangular manifold into a narrowing annular duct and from there through three rectangular openings distributed unevenly around the circumference into the interior of the combustion chamber housing and impinges there on the flame tube.
- the object of the invention is to achieve a uniform air distribution and sufficient cooling of the inner cone, the mixer tube, by converting a tangential flow into an axial flow in the combustion chamber housing, to minimize the pressure loss in the feed area and to further improve the efficiency of the gas turbine.
- the compressor air is supplied through a lateral inlet bend in the shape of an arc to the lower conical part of the combustion chamber housing, the perforated cone.
- the inlet heart connects directly to the intake manifold, in which the compressor air is guided around the perforated cone on both sides.
- the conversion of this tangential flow around a cone into an axial flow through the holes in the perforated cone is achieved in that the cross section of the inlet heart, i.e. the cross-sectional area between the perforated cone and the circumferential inlet heart, in the area between the inlet manifold and the flow divider, is reduced.
- the reduction in cross-section is such that the air speed always remains approximately the same.
- the holes in the hole cone are arranged and designed that the open cross section of the holes increases both from the front to the rear and from top to bottom.
- the conversion of the tangential flow into an axial flow and the resulting uniform cooling of the mixing tube is supported by the six radially arranged ribs. This arrangement prevents the compressor air flowing obliquely upward and backward through the inlet manifold from cooling only a limited area of the mixing tube and from the rear lower area of the mixing tube not being cooled or being cooled insufficiently.
- This arrangement according to the invention achieves optimal cooling of the mixing tube while minimizing the pressure loss in the air supply area.
- Fig. 1 shows a cross section of the lower part of the combustion chamber housing with the inventive design of the air supply area with air inlet manifold (2), inlet heart (1) and perforated cone (5), whereby a uniform air distribution by converting a tangential flow into an axial flow in the combustion chamber housing and a sufficient Cooling of the mixing tube (6) is reached.
- the compressor air represented by arrows is fed through a side inlet elbow (2) in an arc shape to the lower conical part of the combustion chamber housing (perforated cone 5).
- the inlet heart (1) connects to the intake manifold (2), in which the compressor air is guided around the perforated cone (5) on both sides.
- the holes (7) in the perforated cone (5) are arranged and designed so that the open cross section of the holes (7) from front to back and also from enlarged from top to bottom.
- the bores (7) are arranged in the perforated cone (5) on five parallel circumferential lines (8) so that they are each gap.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Air Bags (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Control Of Turbines (AREA)
Abstract
Description
Die Erfindung betrifft ein zylindrisches Brennkammergehäuse einer Gasturbine mit einem unbeschaufelten Eintrittskrümmer mit einem um das Brennkammergehäuse angeordneten sich verengenden Ringkanal zur Einleitung von Verdichterluft durch Öffnungen in das Innere einer Brennkammer.The invention relates to a cylindrical combustion chamber housing of a gas turbine with an unbladed inlet manifold with a narrowing annular channel arranged around the combustion chamber housing for introducing compressor air through openings into the interior of a combustion chamber.
Ein zylindrisches Brennkammergehäuse einer Gasturbine ist aus dem Dokument FR-A-2 439 362 bekannt.A cylindrical combustion chamber housing of a gas turbine is known from document FR-A-2 439 362.
Bei dem bekannten Brennkammergehäuse einer Gasturbine strömt die Verdichterluft aus einem unbeschaufelten Rechteckkrümmer in einen sich verengenden Ringkanal und von dort durch drei ungleichmäßig am Umfang verteilte Rechtecköffnungen ins Innere des Brennkammergehäuses und prallt dort auf das Flammrohr.In the known combustion chamber housing of a gas turbine, the compressor air flows from an unshielded rectangular manifold into a narrowing annular duct and from there through three rectangular openings distributed unevenly around the circumference into the interior of the combustion chamber housing and impinges there on the flame tube.
Bei dieser Konzeption entsteht bereits im Rechteckkrümmer, dem Zuführungsbereich, ein relativ großer Druckverlust und beim Eintritt der Verdichterluft in das Innere der Brennkammer eine ungleichmäßige Strömungsverteilung.With this design, there is already a relatively large pressure loss in the rectangular elbow, the feed area, and an uneven flow distribution when the compressor air enters the interior of the combustion chamber.
Die Aufgabe der Erfindung besteht darin, durch Umwandlung einer Tangentialströmung in eine Axialströmung im Brennkammergehäuse eine gleichmäßige Luftverteilung sowie eine ausreichende Kühlung des Innenkegels, des Mischerrohres, zu erreichen, den Druckverlust im Zuführungsbereich zu minimieren und den Wirkungsgrad der Gasturbine weiter zu verbessern.The object of the invention is to achieve a uniform air distribution and sufficient cooling of the inner cone, the mixer tube, by converting a tangential flow into an axial flow in the combustion chamber housing, to minimize the pressure loss in the feed area and to further improve the efficiency of the gas turbine.
Die Lösung der Aufgabe ist im Hauptanspruch angegeben. Die abhängigen Unteransprüche beziehen sich auf vorteilhafte Ausgestaltungen des Brennkammergehäuses.The solution to the problem is specified in the main claim. The dependent subclaims relate to advantageous refinements of the combustion chamber housing.
Bei der erfindungsgemäßen Vorrichtung wird die Verdichterluft durch einen seitlichen Eintrittskrümmer in Bogenform dem unteren konischen Teil des Brennkammergehäuses, dem Lochkegel, zugeführt. An den Eintrittskrümmer schließt sich direkt das Einlaufherz an, in dem die Verdichterluft um den Lochkegel beidseitig herumgeführt wird.In the device according to the invention, the compressor air is supplied through a lateral inlet bend in the shape of an arc to the lower conical part of the combustion chamber housing, the perforated cone. The inlet heart connects directly to the intake manifold, in which the compressor air is guided around the perforated cone on both sides.
Die Umwandlung dieser Tangentialströmung um einen Konus in eine Axialströmung durch die Bohrungen im Lochkegel wird dadurch erreicht, daß sich der Querschnitt des Einlaufherzens, d.h. die Querschnittsfläche zwischen dem Lochkegel und dem umlaufenden Einlaufherz, im Bereich zwischen Eintrittskrümmer und Strömungsteiler verringert. Die Querschnittsverminderung ist so bemessen, daß die Luftgeschwindigkeit stets annähernd gleich bleibt.The conversion of this tangential flow around a cone into an axial flow through the holes in the perforated cone is achieved in that the cross section of the inlet heart, i.e. the cross-sectional area between the perforated cone and the circumferential inlet heart, in the area between the inlet manifold and the flow divider, is reduced. The reduction in cross-section is such that the air speed always remains approximately the same.
Somit verengt sich der verbleibende Querschnitt des Einlaufherzes zur gegenüberliegenden Seite des Eintrittskrümmers hin stetig. An dieser Seite treffen sich die beiden Luftströmungen am Strömungsteiler wieder. Die durch die Bohrungen des Lochkegels strömende Verdichterluft trifft im Inneren des Brennkammergehäuses auf das ebenfalls konische Mischrohr und kühlt dieses gleichmäßig.The remaining cross-section of the inlet heart thus narrows steadily towards the opposite side of the inlet manifold. On this side the two air flows meet again at the flow divider. The compressor air flowing through the holes in the perforated cone hits the likewise conical mixing tube inside the combustion chamber housing and cools it evenly.
Da sich die Durchflußzahl CDA einer Bohrung mit achsparalleler Strömung (vorderer Bereich des Lochkegels) von der Durchflußzahl CDW einer Bohrung mit wandparalleler Strömung (seitlicher und hinterer Bereich) unterscheidet (CDA > DCW), sind die Bohrungen im Lochkegel so angeordnet und ausgelegt, daß sich der offene Querschnitt der Bohrungen sowohl von vorne nach hinten als auch von oben nach unten vergrößert.Since the flow rate CD A of a hole with parallel flow (front area of the hole cone) differs from the flow rate CD W of a hole with parallel flow (side and rear area) (CD A > DC W ), the holes in the hole cone are arranged and designed that the open cross section of the holes increases both from the front to the rear and from top to bottom.
Die Umwandlung der Tangentialströmung in eine Axialströmung und die dadurch erreichte gleichmäßige Kühlung des Mischrohres wird durch die sechs radial angeordneten Rippen unterstützt. Durch diese Anordnung wird verhindert, daß die von unten durch den Eintrittskrümmer schräg nach oben und nach hinten strömende Verdichterluft nur einen beschränkten Bereich des Mischrohres kühlt und der hintere untere Bereich des Mischrohres nicht oder nur unzureichend gekühlt wird.The conversion of the tangential flow into an axial flow and the resulting uniform cooling of the mixing tube is supported by the six radially arranged ribs. This arrangement prevents the compressor air flowing obliquely upward and backward through the inlet manifold from cooling only a limited area of the mixing tube and from the rear lower area of the mixing tube not being cooled or being cooled insufficiently.
Durch diese erfindungsgemäße Anordnung wird eine optimale Kühlung des Mischrohres unter Minimierung des Druckverlustes des Luftzuführbereiches erreicht.This arrangement according to the invention achieves optimal cooling of the mixing tube while minimizing the pressure loss in the air supply area.
Ausführungsbeispiele der Erfindung werden an Hand von schematischen Zeichnungen erläutert. Es zeigen
- Fig. 1
- einen Querschnitt des Brennkammergehäuses,
- Fig. 2
- eine Draufsicht des Brennkammergehäuses und
- Fig. 3
- die Abwicklung des Lochkegels.
- Fig. 1
- a cross section of the combustion chamber housing,
- Fig. 2
- a plan view of the combustion chamber housing and
- Fig. 3
- the processing of the perforated cone.
Fig. 1 zeigt einen Querschnitt des unteren Teils des Brennkammergehäuses mit der erfindungsgemäßen Gestaltung des Luftzuführbereiches mit Lufteintrittskrümmer (2), Einlaufherz (1) und Lochkegel (5), wodurch eine gleichmäßige Luftverteilung durch eine Umwandlung einer Tangentialströmung in eine Axialströmung im Brennkammergehäuse und eine ausreichende Kühlung des Mischrohres (6) erreicht wird.Fig. 1 shows a cross section of the lower part of the combustion chamber housing with the inventive design of the air supply area with air inlet manifold (2), inlet heart (1) and perforated cone (5), whereby a uniform air distribution by converting a tangential flow into an axial flow in the combustion chamber housing and a sufficient Cooling of the mixing tube (6) is reached.
Die durch Pfeile dargestellte Verdichterluft wird durch einen seitlichen Eintrittskrümmer (2) in Bogenform dem unteren konischen Teil des Brennkammergehäuses (Lochkegel 5) zugeführt. An den Eintrittskrümmer (2) schließt sich das Einlaufherz (1) an, in dem die Verdichterluft um den Lochkegel (5) beidseitig herumgeführt wird.The compressor air represented by arrows is fed through a side inlet elbow (2) in an arc shape to the lower conical part of the combustion chamber housing (perforated cone 5). The inlet heart (1) connects to the intake manifold (2), in which the compressor air is guided around the perforated cone (5) on both sides.
Aus Fig. 2 ist zu ersehen, daß die Umwandlung der Tangentialströmung in eine Axialströmung durch die Bohrungen im Lochkegel (5) dadurch erreicht wird, daß sich die Querschnittsfläche des Einlaufherzes (1), zwischen dem Lochkegel (5) und dem umlaufenden Einlaufherz (1), mit abnehmender Verdichterluftmenge vermindert.From Fig. 2 it can be seen that the conversion of the tangential flow into an axial flow through the holes in the perforated cone (5) is achieved in that the cross-sectional area of the inlet heart (1), between the perforated cone (5) and the circulating inlet heart (1 ), decreases with decreasing compressor air volume.
Somit verengt sich der verbleibende Querschnitt des Einlaufherzes (1) zur gegenüberliegenden Seite des Eintrittskrümmers (2) stetig. An dieser Seite treffen sich die beiden Luftströmungen am Strömungsteiler (4) wieder. Die durch die Bohrungen (7) in Lochkegel (5) strömende Verdichterluft trifft im Inneren des Brennkammergehäuses auf das ebenfalls konische Mischrohr (6) und kühlt dieses gleichmäßig.The remaining cross section of the inlet heart (1) to the opposite side of the inlet manifold (2) thus narrows steadily. On this side, the two air flows meet again at the flow divider (4). The compressor air flowing through the holes (7) in the perforated cone (5) hits the likewise conical mixing tube (6) in the interior of the combustion chamber housing and cools it evenly.
Aus der Abwicklung des Lochkegels (5) in Fig. 3 ist zu erkennen, daß die Bohrungen (7) im Lochkegel (5) so angeordnet und ausgelegt sind, daß sich der offene Querschnitt der Bohrungen (7) von vorne nach hinten und auch von oben nach unten vergrößert.From the development of the perforated cone (5) in Fig. 3 it can be seen that the holes (7) in the perforated cone (5) are arranged and designed so that the open cross section of the holes (7) from front to back and also from enlarged from top to bottom.
Die Bohrungen (7) sind im Lochkegel (5) auf fünf parallel angeordneten Umfangslinien (8) so angebracht, daß sie sich jeweils untereinander auf Lücke befinden.The bores (7) are arranged in the perforated cone (5) on five parallel circumferential lines (8) so that they are each gap.
Die Umwandlung der Tangentialströmung in eine Axialströmung und die dadurch erreichte gleichmäßige Kühlung des Mischrohres (6) wird durch die radial angeordneten Rippen (3) unterstützt. Dadurch wird verhindert, daß die von unten durch den Eintrittskrümmer (2) schräg nach oben und hinten strömende Verdichterluft nur den oberen Bereich des Mischrohres (6) kühlt und der hintere untere Bereich des Mischrohres (6) nicht oder nur unzureichend gekühlt wird.The conversion of the tangential flow into an axial flow and the uniform cooling of the mixing tube (6) achieved thereby is supported by the radially arranged ribs (3). This prevents the compressor air flowing obliquely upwards and backwards through the inlet manifold (2) from cooling only the upper region of the mixing tube (6) and the rear lower region of the mixing tube (6) from not being cooled or only being insufficiently cooled.
Claims (4)
- Cylindrical combustion chamber casing for a gas turbine with an intake elbow which is not bladed, comprising a tapering annular channel disposed around the combustion chamber casing for the introduction of compressor air through apertures into the interior of a combustion chamber, characterised in that an inlet elbow (2) which is mounted laterally in an arcuate form is secured to the lower conical part of the combustion chamber casing (5); in that the inlet elbow (2) merges into a preferably circular inlet core (1), which is conducted around both sides of the lower conical part of the combustion chamber casing (5); and in that the lower conical part of the combustion chamber casing (5) is formed as a conical perforated cone, which is disposed in a circular manner around the inner conical mixing pipe (6).
- Cylindrical combustion chamber casing for a gas turbine according to Claim 1, characterised in that between the perforated cone (5) and the mixing pipe (6) there are provided radially disposed conducting ribs (3).
- Cylindrical combustion chamber casing for a gas turbine according to Claims 1 and 2, characterised in that the bores (7) in the perforated cone (5) are arranged and dimensioned such that the open cross-section of the bores (7) increases from the top to the bottom, both in the area between the inlet elbow (2) to the flow divider (4) and in the perforated cone (5).
- Cylindrical combustion chamber casing for a gas turbine according to Claims 1 to 3, characterised in that the bores (7) in the perforated cone (5) are disposed on a plurality of circumferential lines and the bores (7) are arranged offset to one another.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE4222391A DE4222391C2 (en) | 1992-07-08 | 1992-07-08 | Cylindrical combustion chamber housing of a gas turbine |
DE4222391 | 1992-07-08 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0578048A1 EP0578048A1 (en) | 1994-01-12 |
EP0578048B1 true EP0578048B1 (en) | 1995-08-30 |
Family
ID=6462741
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP93109972A Expired - Lifetime EP0578048B1 (en) | 1992-07-08 | 1993-06-23 | Cylindrical combustion chamber for gas turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US5363653A (en) |
EP (1) | EP0578048B1 (en) |
AT (1) | ATE127209T1 (en) |
CA (1) | CA2099926C (en) |
DE (2) | DE4222391C2 (en) |
DK (1) | DK0578048T3 (en) |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE4238602C2 (en) * | 1992-11-16 | 1996-01-25 | Gutehoffnungshuette Man | Combustion chamber housing of a gas turbine |
DE4328294A1 (en) * | 1993-08-23 | 1995-03-02 | Abb Management Ag | Method for cooling a component and device for carrying out the method |
CA2288555C (en) * | 1998-11-12 | 2007-01-23 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US6412268B1 (en) * | 2000-04-06 | 2002-07-02 | General Electric Company | Cooling air recycling for gas turbine transition duct end frame and related method |
DE10064264B4 (en) * | 2000-12-22 | 2017-03-23 | General Electric Technology Gmbh | Arrangement for cooling a component |
US7192244B2 (en) * | 2004-02-23 | 2007-03-20 | Grande Iii Salvatore F | Bladeless conical radial turbine and method |
US20060010874A1 (en) * | 2004-07-15 | 2006-01-19 | Intile John C | Cooling aft end of a combustion liner |
US7685823B2 (en) * | 2005-10-28 | 2010-03-30 | Power Systems Mfg., Llc | Airflow distribution to a low emissions combustor |
FR2893389B1 (en) * | 2005-11-15 | 2008-02-08 | Snecma Sa | CROSS-SECTIONAL COMBUSTION CHAMBER WALL HAVING MULTIPERFORATION HOLES |
US7870739B2 (en) * | 2006-02-02 | 2011-01-18 | Siemens Energy, Inc. | Gas turbine engine curved diffuser with partial impingement cooling apparatus for transitions |
US9097117B2 (en) * | 2010-11-15 | 2015-08-04 | Siemens Energy, Inc | Turbine transition component formed from an air-cooled multi-layer outer panel for use in a gas turbine engine |
US9133721B2 (en) * | 2010-11-15 | 2015-09-15 | Siemens Energy, Inc. | Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine |
US20140208756A1 (en) * | 2013-01-30 | 2014-07-31 | Alstom Technology Ltd. | System For Reducing Combustion Noise And Improving Cooling |
US9163837B2 (en) | 2013-02-27 | 2015-10-20 | Siemens Aktiengesellschaft | Flow conditioner in a combustor of a gas turbine engine |
CN104296160A (en) * | 2014-09-22 | 2015-01-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Flow guide bush of combustion chamber of combustion gas turbine and with cooling function |
US10139109B2 (en) * | 2016-01-07 | 2018-11-27 | Siemens Energy, Inc. | Can-annular combustor burner with non-uniform airflow mitigation flow conditioner |
JP2019534409A (en) * | 2016-09-01 | 2019-11-28 | アッディティブ ロケット コーポレーション | Additional manufactured combustion engine |
US10774664B2 (en) * | 2017-06-08 | 2020-09-15 | General Electric Company | Plenum for cooling turbine flowpath components and blades |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB637223A (en) * | 1946-01-29 | 1950-05-17 | Gen Electric | Improvements in and relating to combustion units particularly for use in gas turbinesystems |
US2541170A (en) * | 1946-07-08 | 1951-02-13 | Kellogg M W Co | Air intake arrangement for air jacketed combustion chambers |
US2669090A (en) * | 1951-01-13 | 1954-02-16 | Lanova Corp | Combustion chamber |
US2692478A (en) * | 1951-02-24 | 1954-10-26 | Boeing Co | Turbine burner incorporating removable burner liner |
US2745250A (en) * | 1952-09-26 | 1956-05-15 | Gen Electric | Reverse vortex combustion chamber |
GB736635A (en) * | 1953-06-25 | 1955-09-14 | Lucas Industries Ltd | Liquid fuel combustion apparatus |
DE1123868B (en) * | 1958-08-26 | 1962-02-15 | Schweizerische Lokomotiv | Combustion chamber, especially for gas turbines |
DE1224095B (en) * | 1962-07-24 | 1966-09-01 | Prvni Brnenska Strojirna Zd Y | Gas turbine combustor |
US3485442A (en) * | 1965-09-13 | 1969-12-23 | Caterpillar Tractor Co | Gas turbine engines |
US3368604A (en) * | 1966-06-14 | 1968-02-13 | American Air Filter Co | Combustion apparatus |
DE2845588A1 (en) * | 1978-10-19 | 1980-04-24 | Motoren Turbinen Union | COMBUSTION CHAMBER FOR GAS TURBINE ENGINES |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
JPH0752014B2 (en) * | 1986-03-20 | 1995-06-05 | 株式会社日立製作所 | Gas turbine combustor |
DE3640894C2 (en) * | 1986-11-29 | 1997-05-28 | Klein Schanzlin & Becker Ag | Inlet housing for centrifugal pump |
CA1309873C (en) * | 1987-04-01 | 1992-11-10 | Graham P. Butt | Gas turbine combustor transition duct forced convection cooling |
-
1992
- 1992-07-08 DE DE4222391A patent/DE4222391C2/en not_active Expired - Lifetime
-
1993
- 1993-06-23 DE DE59300530T patent/DE59300530D1/en not_active Expired - Lifetime
- 1993-06-23 DK DK93109972.5T patent/DK0578048T3/en active
- 1993-06-23 AT AT93109972T patent/ATE127209T1/en not_active IP Right Cessation
- 1993-06-23 EP EP93109972A patent/EP0578048B1/en not_active Expired - Lifetime
- 1993-07-06 CA CA002099926A patent/CA2099926C/en not_active Expired - Fee Related
- 1993-07-07 US US08/088,311 patent/US5363653A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
EP0578048A1 (en) | 1994-01-12 |
DE59300530D1 (en) | 1995-10-05 |
ATE127209T1 (en) | 1995-09-15 |
CA2099926C (en) | 2001-02-20 |
DE4222391A1 (en) | 1994-01-20 |
DE4222391C2 (en) | 1995-04-20 |
US5363653A (en) | 1994-11-15 |
CA2099926A1 (en) | 1994-01-09 |
DK0578048T3 (en) | 1995-12-04 |
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