EP2699848A1 - Combustion chamber housing and gas turbine equipped therewith - Google Patents

Combustion chamber housing and gas turbine equipped therewith

Info

Publication number
EP2699848A1
EP2699848A1 EP12717246.8A EP12717246A EP2699848A1 EP 2699848 A1 EP2699848 A1 EP 2699848A1 EP 12717246 A EP12717246 A EP 12717246A EP 2699848 A1 EP2699848 A1 EP 2699848A1
Authority
EP
European Patent Office
Prior art keywords
guide ribs
combustion chamber
tube
chamber housing
flame tube
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.)
Granted
Application number
EP12717246.8A
Other languages
German (de)
French (fr)
Other versions
EP2699848B1 (en
Inventor
Emil Aschenbruck
Reiner Brinkmann
Stefan Hoffmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2699848A1 publication Critical patent/EP2699848A1/en
Application granted granted Critical
Publication of EP2699848B1 publication Critical patent/EP2699848B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M9/00—Baffles or deflectors for air or combustion products; Flame shields
    • F23M9/02—Baffles or deflectors for air or combustion products; Flame shields in air inlets
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to a combustion chamber housing according to the preamble of claim 1 and a gas turbine equipped with such a combustion chamber housing.
  • a combustion chamber housing and a gas turbine of the type mentioned above are e.g. from DE 10 2006 042 124 A1. The one described there
  • Combustor housing is part of a combustion chamber of the gas turbine and has a flame tube and a cladding tube or impact grid, which surrounds the flame tube and which in its wall a plurality of
  • inflowing compressed air can penetrate radially into a gap formed between the sheath tube and the flame tube.
  • Combustion chambers are designed as individual modules or as annularly arranged individual burners or as annular combustion chambers. Except for the
  • Ring combustion chambers these types always have an internal, cylindrical flame tube.
  • the combustion air is first sucked in atmospherically and then compressed in a compressor of a gas generator.
  • the compressor may be radial or axial.
  • the combustion air is then greatly deflected in order to achieve an inflow into the combustion zone. In other words, the combustion air is first the
  • Combustion chamber radially in between the casing tube and flame tube supplied space formed and then deflected so that an axial inflow of the burner takes place.
  • the invention is based on the object, a combustion chamber housing according to the preamble of claim 1 and a gas turbine equipped therewith
  • a combustion chamber housing in particular for a gas turbine, is provided, which is a preferably circular-cylindrical flame tube and a preferably circular-cylindrical one
  • Has jacket tube or impact grid which receives the flame tube and surrounds and which in its wall a plurality of
  • the invention Combustor housing is characterized by a plurality of in the
  • Casing tube extending longitudinal channels with preferably each
  • the transverse to the flow direction of the air flowing in the operation case guide ribs cause the flow around the flame tube is interrupted or prevented.
  • the air flow can distribute more evenly and the cooling of the flame tube is less disturbed.
  • the cooling and combustion air is channel-shaped after the deflection from radial to axial flow, so that the inflow to a subsequent combustion zone can be made homogeneous.
  • combustion chamber of a gas turbine according to the invention formed a particularly homogeneous fuel-air mixture, whereby the flame during the combustion process stable in the center of
  • Combustion chamber remains A fluctuation or fluctuation of the flame would cause a local temperature increase of the surrounding components and thus a possible overuse, which is prevented by the Leitrippen.
  • each guide rib is attached to the sheath tube.
  • each guide rib preferably extends radially in such a way that a gap is formed between the guide rib and the flame tube
  • the Letrippen are each strip-shaped, with their respective width extending radially and their respective length axially or in the longitudinal direction of the sheath tube and flame tube.
  • the thickness dimension of the respective guide ribs is preferably about 3 mm.
  • the guide ribs and the passage openings formed in the wall of the sheathing tube are arranged so that the guide ribs do not close any of the passage openings. This is advantageous an optimal or unobstructed radial inflow of air in the
  • the guide ribs are arranged at different circumferential angular distances from one another in the intermediate space.
  • the Angular spacing preferably varies in a range of about 28 degrees to about 126 degrees.
  • the guide ribs comprise a first group of guide ribs and a second group of guide ribs, wherein the first group of guide ribs are arranged in a predetermined first arrangement pattern with respect to their mutual circumferential angular spacing, and wherein the second group of guide ribs are mutually circumferential
  • Angular spacing are arranged in a second arrangement pattern, which is a reflection of the first arrangement pattern on an axis of symmetry of the fire tube.
  • the symmetry axis preferably extends in cross section through the center of the flame tube.
  • a gas turbine having a combustion chamber housing according to one, several or all of the previously described preferred embodiments of the invention is provided in any conceivable combination.
  • FIG. 1 shows a perspective partially broken view of a
  • FIG. 2 shows an end view of the combustion chamber housing of FIG. 1, but without a flame tube
  • FIG. 3 shows a sectional view of the combustion-chamber housing of FIG. 1, seen along a line A-A in FIG.
  • FIG. 4 shows in two cross-sectional views a comparison of the air flow and pressure distributions in the combustion chamber housing of FIG. 1 with and without guide ribs.
  • FIGS. 1 to 4 a gas turbine 1 (not shown in full) with a combustion chamber housing 10 is shown in FIGS. 1 to 4,
  • the combustion chamber housing 10 of the gas turbine 1 has a circular cylindrical flame tube 20 and a circular cylindrical sheath or baffle 30 which receives and surrounds the flame tube 20 and which has in its wall a plurality of uniformly distributed around the circumference through openings 31, on the outer circumference the
  • Jacket tube 30 flowing up through a compressor (not shown) of the gas turbine 1 compressed air (cooling and combustion air) can penetrate radially into a formed between the sheath tube 30 and the flame tube 20 circular cylindrical space 40.
  • a plurality in this case exactly eight) distributed circumferentially of the two tubes (flame tube 20 and sheath tube 30) arranged identical guide ribs 50 are provided, each radially between
  • Sheath tube 30 and flame tube 20 and parallel to and extend along a longitudinal direction LR of sheath tube 30 and flame tube 20 so that the gap 40 through the guide ribs 50 in a plurality of
  • the guide ribs 50 reliably prevent that in the operating case on the
  • the guide ribs 50 are attached (e.g., welded) to the inner circumference of the jacket tube 30, with each guide rib 50 extending radially such that a gap S is formed between the guide rib 50 and the flame tube 20.
  • the gap S has just such a radial width that during operation of the gas turbine. 1
  • Guide ribs 50 can be compensated for on the flame tube 20.
  • the guide ribs 50 are each in the form of a sheet metal strip, with their respective width extending radially and their respective length axially or in the longitudinal direction LR of the casing tube 30 and the flame tube 20.
  • Thickness of the respective guide ribs 50 is about 3 mm.
  • the guide ribs 50 and those formed in the wall of the jacket tube 30 are
  • Interspace 40 is arranged.
  • the guide ribs 50 in this case have a first group of guide ribs 50 (which are arranged in FIG. 2 to the left of an axis of symmetry Y of the flame tube 20) and a second group of guide ribs 50 (which are arranged to the right of the symmetry axis Y in FIG.
  • the first group of guide ribs 50 are arranged in a predetermined first arrangement pattern with respect to their mutual circumferential angular distance
  • the second group of guide ribs 50 being arranged in a second arrangement pattern with respect to their mutual circumferential angular distance, which is a reflection of the first arrangement pattern at the
  • Symmetry axis Y represents
  • the first and second arrangement patterns could also be completely different his.
  • the specific realization of the first and second arrangement pattern or of the respective angular spacing of the guide ribs 50 can be different from the respective example B.
  • Combustion chamber housing according to the upper view in Figure 4 without guide fins 50 and the combustion chamber housing according to the bottom in Figure 4 representation according to the invention with guide ribs 50 is executed.
  • the guide ribs 50 which are transverse to the direction of flow of the incoming air during operation of the gas turbine 1 produce substantially homogeneous airflow and flow conditions in the intermediate space 40 due to the resulting obstruction of the circumferential flow around the flame tube 20 Pressure conditions, whereby a uniform distribution of the incoming air reaches around the flame tube 20 and the cooling of the flame tube 20 is improved.
  • the air is channel-shaped after the deflection from radial to axial flow, so that the inflow to the subsequent combustion zone is homogeneous LIST OF REFERENCE NUMBERS

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a combustion chamber housing (10) and to a gas turbine (1) equipped therewith, wherein the combustion chamber housing has a flame tube (20) and a cladding tube (30) which surrounds the flame tube and which in the wall thereof has a plurality of through-holes (31) via which air flowing on the outside onto the cladding tube can radially penetrate into an intermediate space (40) formed between the cladding tube and the flame tube. The invention assures uniform distribution of the inflowing air around the flame tube. This is achieved, among other things, by providing a plurality of guide ribs (50), which are distributed in the intermediate space on the circumference of the two tubes and which each extend radially between the cladding tube and flame tube and parallel to a longitudinal direction (LR) of the two tubes such that the intermediate space is divided by the guide ribs into several longitudinal channels (41).

Description

Brennkammergehäuse und damit ausgerüstete Gasturbine  Combustor housing and thus equipped gas turbine
Die Erfindung betrifft ein Brennkammergehäuse gemäß dem Oberbegriff des Anspruchs 1 sowie eine mit einem solchen Brennkammergehäuse ausgerüstete Gasturbine. The invention relates to a combustion chamber housing according to the preamble of claim 1 and a gas turbine equipped with such a combustion chamber housing.
Ein Brennkammergehäuse und eine Gasturbine der eingangsgenannten Art sind z.B. aus DE 10 2006 042 124 A1 bekannt. Das dort beschriebene A combustion chamber housing and a gas turbine of the type mentioned above are e.g. from DE 10 2006 042 124 A1. The one described there
Brennkammergehäuse ist Bestandteil einer Brennkammer der Gasturbine und weist ein Flammrohr und ein Ummantelungsrohr bzw. Prallgitter auf, welches das Flammrohr umgibt und welches in seiner Wandung eine Mehrzahl von  Combustor housing is part of a combustion chamber of the gas turbine and has a flame tube and a cladding tube or impact grid, which surrounds the flame tube and which in its wall a plurality of
Durchgangsöffnungen hat, über die außen auf das Ummantelungsrohr Through openings has, on the outside of the sheath tube
aufströmende komprimierte Luft radial in einen zwischen dem Ummantelungsrohr und dem Flammrohr gebildeten Zwischenraum eindringen kann. inflowing compressed air can penetrate radially into a gap formed between the sheath tube and the flame tube.
Brennkammern werden als Einzelmodule oder als ringförmig angeordnete Einzelbrenner oder als Ringbrennkammern ausgeführt. Bis auf die Combustion chambers are designed as individual modules or as annularly arranged individual burners or as annular combustion chambers. Except for the
Ringbrennkammern haben diese Typen immer ein innen liegendes, zylindrisch aufgebautes Flammrohr. Ring combustion chambers, these types always have an internal, cylindrical flame tube.
In einer wie oben genannten Gasturbine wird die Verbrennungsluft zunächst atmosphärisch angesaugt und dann in einem Kompressor eines Gasgenerators verdichtet. Der Kompressor kann radial oder axial ausgeführt sein. In der strömungsabwärts darauf folgenden Brennkammer wird die Verbrennungsluft dann stark umgelenkt, um eine Zuströmung in die Verbrennungszone zu erreichen. Mit anderen Worten wird die Verbrennungsluft zunächst der In a gas turbine as mentioned above, the combustion air is first sucked in atmospherically and then compressed in a compressor of a gas generator. The compressor may be radial or axial. In the downstream following combustion chamber, the combustion air is then greatly deflected in order to achieve an inflow into the combustion zone. In other words, the combustion air is first the
Brennkammer radial in den zwischen Ummantelungsrohr und Flammrohr gebildeten Zwischenraum zugeführt und anschließend umgelenkt, so dass eine axiale Zuströmung des Brenners stattfindet. Combustion chamber radially in between the casing tube and flame tube supplied space formed and then deflected so that an axial inflow of the burner takes place.
In dem Zwischenraum kommt es zu einer umfänglichen bzw. rotierenden In the space there is a circumferential or rotating
Umströmung des meist kreiszylindrischen Flammrohrs, wodurch bezüglich der Druckverteilung bzw. Strömungsverteilung der Verbrennungsluft Staupunkte und Nachlaufdellen entstehen. Wenn bei einer solchen inhomogenen Flow around the usually circular cylindrical flame tube, whereby with respect to the pressure distribution or flow distribution of the combustion air stagnation points and trailing dents arise. If at such an inhomogeneous
Massenstromverteilung die Strömung nun wie beschrieben zusätzlich stark umgelenkt wird, bleibt diese Inhomogenität erhalten. Dadurch werden Mass flow distribution, the flow is now additionally strongly deflected as described, this inhomogeneity is maintained. This will be
stromabwärts liegende Bauteile ungleichmäßig gekühlt und es kommt in der Verbrennungszone zu Instabilitäten, weil der Luftanteil schwankt. Downstream components cooled unevenly and it comes in the combustion zone to instabilities, because the air content fluctuates.
Der Erfindung liegt die Aufgabe zugrunde, ein Brennkammergehäuse gemäß dem Oberbegriff des Anspruchs 1 und eine damit ausgerüstete Gasturbine The invention is based on the object, a combustion chamber housing according to the preamble of claim 1 and a gas turbine equipped therewith
bereitzustellen, bei denen eine gleichmäßigere Verteilung der einströmenden Luft um das Flammrohr gewährleistet ist. to provide, in which a more uniform distribution of the incoming air is ensured around the flame tube.
Dies wird mit einem Brennkammergehäuse gemäß Anspruch 1 bzw. mit einer Gasturbine gemäß Anspruch 10 erreicht. Weiterbildungen der Erfindung sind in den abhängigen Ansprüchen definiert This is achieved with a combustion chamber housing according to claim 1 or with a gas turbine according to claim 10. Further developments of the invention are defined in the dependent claims
Gemäß einem ersten Aspekt der Erfindung wird ein Brennkammergehäuse, insbesondere für eine Gasturbine, bereitgestellt, welches ein bevorzugt kreiszylindrisches Flammrohr und ein bevorzugt kreiszylindrisches According to a first aspect of the invention, a combustion chamber housing, in particular for a gas turbine, is provided, which is a preferably circular-cylindrical flame tube and a preferably circular-cylindrical one
Ummantelungsrohr bzw. Prallgitter aufweist, welches das Flammrohr aufnimmt und umgibt und welches in seiner Wandung eine Mehrzahl von Has jacket tube or impact grid, which receives the flame tube and surrounds and which in its wall a plurality of
Durchgangsöffnungen hat, über die außen auf das Ummantelungsrohr aufströmende komprimierte Luft (Kühl- und Verbrennungsluft) radial in einen zwischen dem Ummantelungsrohr und dem Flammrohr gebildeten bevorzugt kreiszylinderförmigen Zwischenraum eindringen kann. Das erfindungsgemäße Brennkammergehäuse zeichnet sich aus durch eine Mehrzahl von in dem Through openings has, on the outside of the sheath tube aufströmende compressed air (cooling and combustion air) can penetrate radially into a preferably circular cylindrical space formed between the sheath tube and the flame tube. The invention Combustor housing is characterized by a plurality of in the
Zwischenraum umfänglich der beiden Rohre (Flammrohr und Ummantelungsrohr) verteilt angeordneten Leitrippen, die sich jeweils radial zwischen Intermediate space circumferentially of the two tubes (flame tube and sheathing tube) distributed guide ribs, each radially between
Ummantelungsrohr und Flammrohr sowie parallel zu und entlang einer Sheath tube and flame tube and parallel to and along a
Längsrichtung von Ummantelungsrohr und Flammrohr erstrecken, so dass der Zwischenraum durch die Leitrippen in mehrere sich bevorzugt im Wesentlichen über die gesamte mit Durchgangsöffnungen versehene Länge des Extend longitudinally of the shroud tube and the flame tube, so that the gap through the guide ribs in a plurality of preferably substantially over the entire provided with through holes length of
Ummantelungsrohrs erstreckende Längskanäle mit bevorzugt jeweils Casing tube extending longitudinal channels with preferably each
kreisringsektorförmigem Querschnitt unterteilt ist. is divided into a circular sector-shaped cross section.
Die quer zur Umströmungsrichtung der im Betriebsfall einströmenden Luft stehenden Leitrippen bewirken, dass die Umströmung des Flammrohrs unterbrochen bzw. verhindert wird. Dadurch kann sich die Luftströmung gleichmäßiger verteilen und die Kühlung des Flammrohres wird weniger gestört. Zusätzlich wird die Kühl- und Verbrennungsluft nach der Umlenkung von radialer auf axiale Strömung kanalförmig geführt, so dass die Zuströmung zu einer nachfolgenden Verbrennungszone homogen erfolgen kann. The transverse to the flow direction of the air flowing in the operation case guide ribs cause the flow around the flame tube is interrupted or prevented. As a result, the air flow can distribute more evenly and the cooling of the flame tube is less disturbed. In addition, the cooling and combustion air is channel-shaped after the deflection from radial to axial flow, so that the inflow to a subsequent combustion zone can be made homogeneous.
Durch die optimierte Zuströmung der Luft kann in einer mit dem Due to the optimized inflow of air can be in one with the
erfindungsgemäßen Brennkammergehäuse ausgebildeten Brennkammer einer Gasturbine ein besonders homogenes Brennstoff-Luft-Gemisch gebildet werden, wodurch die Flamme beim Verbrennungsprozess stabil im Zentrum der combustion chamber of a gas turbine according to the invention formed a particularly homogeneous fuel-air mixture, whereby the flame during the combustion process stable in the center of
Brennkammer bleibt Eine Schieflage bzw. Fluktuation der Flamme würde einen lokalen Temperaturanstieg der umliegenden Bauteile bewirken und damit eine eventuelle Überbeanspruchung, was durch die Leitrippen verhindert wird. Combustion chamber remains A fluctuation or fluctuation of the flame would cause a local temperature increase of the surrounding components and thus a possible overuse, which is prevented by the Leitrippen.
Im Ergebnis werden mit der Verwendung des erfindungsgemäß ausgestalteten Brennkammergehäuses in einer Brennkammer einer Gasturbine As a result, with the use of the inventively designed combustion chamber housing in a combustion chamber of a gas turbine
Ungteichmäßigkeiten der Luftzufuhr minimiert, so dass ein Betrieb der Imbalances of the air supply minimized, allowing operation of the
Brennkammer mit maximaler Auslegungstemperatur uneingeschränkt erfolgen kann. Bevorzugt sind gemäß der Erfindung die Leitrippen am Ummantelungsrohr angebracht Außerdem erstreckt sich bevorzugt jede Leitrippe radial so, dass zwischen Leitrippe und Flammrohr ein Spalt gebildet ist Combustion chamber with maximum design temperature can be carried out without restriction. Preferably, according to the invention, the guide ribs are attached to the sheath tube. In addition, each guide rib preferably extends radially in such a way that a gap is formed between the guide rib and the flame tube
Der Spalt ist vorteilhaft, um aufgrund unterschiedlicher Material- und The gap is advantageous to due to different material and
Wärmeausdehnungseigenschaften mögliche Verzüge oder Spannungen zu vermeiden. Durch die Spalte hindurch auftretende Querströmungen können vernachlässigt werden, das sich die Strömung immer radial nach außen auf die Seite (Innenumfang des Ummantelungsrohrs) anlegt, an der auch die Thermal expansion properties to avoid possible distortion or tension. Through the column occurring cross flows can be neglected, the flow always applies radially outward on the side (inner circumference of the sheath tube), on which also the
Strömungsleitrippen angebracht sind. Flow guide ribs are attached.
Bevorzugt sind gemäß der Erfindung die Lettrippen jeweils streifenförmig ausgebildet, wobei sich deren jeweilige Breite radial und deren jeweilige Länge axial bzw. in Längsrichtung von Ummantelungsrohr und Flammrohr erstrecken. Die Dickenabmessung der jeweiligen Leitrippen beträgt bevorzugt etwa 3 mm. Preferably, according to the invention, the Letrippen are each strip-shaped, with their respective width extending radially and their respective length axially or in the longitudinal direction of the sheath tube and flame tube. The thickness dimension of the respective guide ribs is preferably about 3 mm.
Bevorzugt sind gemäß der Erfindung die Leitrippen und die in der Wandung des Ummantelungsrohrs ausgebildeten Durchgangsöffnungen so angeordnet, dass die Leitrippen keine der Durchgangsöffnungen verschließen. Damit wird vorteilhaft eine optimale bzw. unbehinderte radiale Zuströmung der Luft in den Preferably, according to the invention, the guide ribs and the passage openings formed in the wall of the sheathing tube are arranged so that the guide ribs do not close any of the passage openings. This is advantageous an optimal or unobstructed radial inflow of air in the
Zwischenraum gewährleistet. Space guaranteed.
Gemäß einer bevorzugten Ausgestaltung der Erfindung beträgt die in dem According to a preferred embodiment of the invention is in the
Zwischenraum vorgesehene Anzahl von Leitrippen genau acht, wobei alle Space provided number of baffles exactly eight, with all
Leitrippen zueinander identisch ausgebildet sind Guide ribs are identical to each other
Bevorzugt sind gemäß der Erfindung die Leitrippen mit unterschiedlichem umfänglichen Winkelabstand voneinander in dem Zwischenraum angeordnet. Der Winkelabstand variiert bevorzugt in einem Bereich von etwa 28 Grad bis etwa 126 Grad. Preferably, according to the invention, the guide ribs are arranged at different circumferential angular distances from one another in the intermediate space. The Angular spacing preferably varies in a range of about 28 degrees to about 126 degrees.
Bevorzugt weisen gemäß der Erfindung die Leitrippen eine erste Gruppe von Leitrippen und eine zweite Gruppe von Leitrippen auf , wobei die erste Gruppe von Leitrippen bezüglich ihres gegenseitigen umfänglichen Winkelabstands in einem vorbestimmten ersten Anordnungsmuster angeordnet sind, und wobei die zweite Gruppe von Leitrippen bezüglich ihres gegenseitigen umfänglichen Preferably, according to the invention, the guide ribs comprise a first group of guide ribs and a second group of guide ribs, wherein the first group of guide ribs are arranged in a predetermined first arrangement pattern with respect to their mutual circumferential angular spacing, and wherein the second group of guide ribs are mutually circumferential
Winkelabstands in einem zweiten Anordnungsmuster angeordnet sind, weiches eine Spiegelung des ersten Anordnungsmusters an einer Symmetrieachse des Flammrohrs darstellt. Die Symmetrieachse erstreckt sich bevorzugt im Querschnitt gesehen durch den Mittelpunkt des Flammrohrs. Angular spacing are arranged in a second arrangement pattern, which is a reflection of the first arrangement pattern on an axis of symmetry of the fire tube. The symmetry axis preferably extends in cross section through the center of the flame tube.
Gemäß einem zweiten Aspekt der Erfindung wird eine Gasturbine mit einem Brennkammergehäuse gemäß einer, mehreren oder allen zuvor beschriebenen bevorzugten Ausgestaltungen der Erfindung in jeder denkbaren Kombination bereitgestellt. According to a second aspect of the invention, a gas turbine having a combustion chamber housing according to one, several or all of the previously described preferred embodiments of the invention is provided in any conceivable combination.
Die Erfindung erstreckt sich ausdrücklich auch auf solche Ausführungsformen, welche nicht durch Merkmalskombinationen aus expliziten Rückbezügen der Ansprüche gegeben sind, womit die offenbarten Merkmale der Erfindung - soweit dies technisch sinnvoll ist - beliebig miteinander kombiniert sein können. The invention expressly extends to such embodiments, which are not given by combinations of features of explicit back references of the claims, whereby the disclosed features of the invention - as far as is technically feasible - can be combined with each other.
Im Folgenden wird die Erfindung anhand einer bevorzugten Ausführungsform und unter Bezugnahme auf die beigefügten Figuren detaillierter beschrieben. In the following the invention will be described in more detail by means of a preferred embodiment and with reference to the attached figures.
Fig.1 zeigt eine perspektivische teilweise gebrochene Ansicht eines 1 shows a perspective partially broken view of a
Brennkammergehäuses einer Brennkammer einer Gasturbine gemäß einer Ausführungsform der Erfindung. Fig 2 zeigt eine Stirnansicht des Brennkammergehäuses von Fig.1 , jedoch ohne Flammrohr Combustion chamber of a combustion chamber of a gas turbine according to an embodiment of the invention. FIG. 2 shows an end view of the combustion chamber housing of FIG. 1, but without a flame tube
Fig.3 zeigt eine Schnittansicht des Brennkammergehäuses von Fig.1 , gesehen entlang einer Linie A-A in Fig.2.  FIG. 3 shows a sectional view of the combustion-chamber housing of FIG. 1, seen along a line A-A in FIG.
Fig 4 zeigt in zwei Querschnittsansichten einen Vergleich der Luftströmungsund Druckverteilungen in dem Brennkammergehäuse von Fig.1 mit und ohne Leitrippen. 4 shows in two cross-sectional views a comparison of the air flow and pressure distributions in the combustion chamber housing of FIG. 1 with and without guide ribs.
Nun wird unter Bezugnahme auf die Figuren 1 bis 4 eine Gasturbine 1 (nicht vollständig dargestellt) mit einem Brennkammergehäuse 10 gemäß einer Referring now to FIGS. 1 to 4, a gas turbine 1 (not shown in full) with a combustion chamber housing 10 is shown in FIG
Ausführungsform der Erfindung beschrieben. Embodiment of the invention described.
Das Brennkammergehäuse 10 der Gasturbine 1 weist ein kreiszylindrisches Flammrohr 20 und ein kreiszylindrisches Ummantelungsrohr bzw. Prallgitter 30 auf, welches das Flammrohr 20 aufnimmt und umgibt und welches in seiner Wandung eine Mehrzahl von gleichmäßig um den Umfang herum verteilten Durchgangsöffnungen 31 hat, über die außenumfänglich auf das The combustion chamber housing 10 of the gas turbine 1 has a circular cylindrical flame tube 20 and a circular cylindrical sheath or baffle 30 which receives and surrounds the flame tube 20 and which has in its wall a plurality of uniformly distributed around the circumference through openings 31, on the outer circumference the
Ummantelungsrohr 30 aufströmende durch einen Kompressor (nicht gezeigt) der Gasturbine 1 komprimierte Luft (Kühl- und Verbrennungsluft) radial in einen zwischen dem Ummantelungsrohr 30 und dem Flammrohr 20 gebildeten kreiszylinderförmigen Zwischenraum 40 eindringen kann. Jacket tube 30 flowing up through a compressor (not shown) of the gas turbine 1 compressed air (cooling and combustion air) can penetrate radially into a formed between the sheath tube 30 and the flame tube 20 circular cylindrical space 40.
In dem Zwischenraum 40 sind eine Mehrzahl (hier genau acht) von umfänglich der beiden Rohre (Flammrohr 20 und Ummantelungsrohr 30) verteilt angeordneten identischen Leitrippen 50 vorgesehen, die sich jeweils radial zwischen In the intermediate space 40, a plurality (in this case exactly eight) distributed circumferentially of the two tubes (flame tube 20 and sheath tube 30) arranged identical guide ribs 50 are provided, each radially between
Ummantelungsrohr 30 und Flammrohr 20 sowie parallel zu und entlang einer Längsrichtung LR von Ummantelungsrohr 30 und Flammrohr 20 erstrecken, so dass der Zwischenraum 40 durch die Leitrippen 50 in mehrere sich im  Sheath tube 30 and flame tube 20 and parallel to and extend along a longitudinal direction LR of sheath tube 30 and flame tube 20 so that the gap 40 through the guide ribs 50 in a plurality of
Wesentlichen über die gesamte mit Durchgangsöffnungen 31 versehene Länge des Ummantelungsrohrs 30 erstreckende Längskanäle 41 mit jeweils Essentially over the entire provided with through holes 31 length the sheath tube 30 extending longitudinal channels 41, respectively
kreisringsektorförmigem Querschnitt unterteilt ist is divided into a circular sector-shaped cross section
Die Leitrippen 50 verhindern zuverlässig, dass die im Betriebsfall über die The guide ribs 50 reliably prevent that in the operating case on the
Durchgangsöffnungen 31 radial einströmende Luft im Zwischenraum 40 eine umfängliche bzw. um das Flammrohr 20 rotierende Strömungskomponente erhält. Dadurch kann sich die Luftströmung gleichmäßiger um das Flammrohr 20 verteilen und die Kühlung des Flammrohres 20 wird verbessert Zusätzlich wird die Luft nach der Umlenkung (durch das Auftreffen auf das Flammrohr 20) von radialer auf axiale Strömung kanalisiert in den Längskanälen 41 geführt, so dass die Zuströmung zu einer nachfolgenden Verbrennungszone (nicht gezeigt) homogen erfolgen kann. Through openings 31 radially inflowing air in the intermediate space 40 receives a circumferential or around the flame tube 20 rotating flow component. As a result, the air flow can be distributed more uniformly around the flame tube 20 and the cooling of the flame tube 20 is improved. In addition, the air after the deflection (by hitting the flame tube 20) is channeled from radial to axial flow in the longitudinal channels 41, so that the Inflow to a subsequent combustion zone (not shown) can be made homogeneous.
Die Leitrippen 50 sind am Innenumfang des Urnmantelungsrohr 30 angebracht (z.B. angeschweißt), wobei sich jede Leitrippe 50 radial so erstreckt, dass zwischen Leitrippe 50 und Flammrohr 20 ein Spalt S gebildet ist. Der Spalt S hat gerade eine solche radiale Weite, dass im Betrieb der Gasturbine 1 The guide ribs 50 are attached (e.g., welded) to the inner circumference of the jacket tube 30, with each guide rib 50 extending radially such that a gap S is formed between the guide rib 50 and the flame tube 20. The gap S has just such a radial width that during operation of the gas turbine. 1
unterschiedliche wärmebedingte Materialausdehnungen von Flammrohr 20, Urnmantelungsrohr 30 und Leitrippen 50 ohne unter Druck Aufsetzen der different heat-related material expansions of flame tube 20, Urnmantelungsrohr 30 and baffles 50 without pressurizing the
Leitrippen 50 auf dem Flammrohr 20 kompensiert werden können. Guide ribs 50 can be compensated for on the flame tube 20.
Die Leitrippen 50 sind jeweils in Form eines Blechstreifens ausgebildet, wobei sich deren jeweilige Breite radial und deren jeweilige Länge axial bzw. in Längsrichtung LR von Urnmantelungsrohr 30 und Flammrohr 20 erstrecken. Die The guide ribs 50 are each in the form of a sheet metal strip, with their respective width extending radially and their respective length axially or in the longitudinal direction LR of the casing tube 30 and the flame tube 20. The
Dickenabmessung der jeweiligen Leitrippen 50 beträgt dabei etwa 3 mm. Thickness of the respective guide ribs 50 is about 3 mm.
Wie insbesondere aus Fig.3 (linke Hälfte der Figur) ersichtlich, sind die Leitrippen 50 und die in der Wandung des Ummantelungsrohrs 30 ausgebildeten As can be seen in particular from FIG. 3 (left half of the figure), the guide ribs 50 and those formed in the wall of the jacket tube 30 are
Durchgangsöffnungen 31 so angeordnet, dass die Leitrippen 50 keine der Durchgangsöffnungen 31 verschließen. Wie insbesondere aus den Figuren 1 und 2 ersichtlich, sind die Leitrippen 50 mit unterschiedlichem umfänglichen Winkelabstand voneinander in dem Through openings 31 arranged so that the guide ribs 50 close any of the through holes 31. As can be seen in particular from Figures 1 and 2, the guide ribs 50 are at different circumferential angular distance from each other in the
Zwischenraum 40 angeordnet. Interspace 40 is arranged.
Die Leitrippen 50 weisen dabei eine erste Gruppe von Leitrippen 50 (die in Fig.2 links einer Symmetrieachse Y des Flammrohrs 20 angeordnet sind) und eine zweite Gruppe von Leitrippen 50 (die in Fig .2 rechts der Symmetrieachse Y angeordnet sind) auf. Gemäß der gezeigten Ausführungsform der Erfindung sind die erste Gruppe von Leitrippen 50 bezüglich ihres gegenseitigen umfänglichen Winkelabstands in einem vorbestimmten ersten Anordnungsmuster angeordnet, wobei die zweite Gruppe von Leitrippen 50 bezüglich ihres gegenseitigen umfänglichen Winkelabstands in einem zweiten Anordnungsmuster angeordnet sind, welches eine Spiegelung des ersten Anordnungsmusters an der The guide ribs 50 in this case have a first group of guide ribs 50 (which are arranged in FIG. 2 to the left of an axis of symmetry Y of the flame tube 20) and a second group of guide ribs 50 (which are arranged to the right of the symmetry axis Y in FIG. According to the shown embodiment of the invention, the first group of guide ribs 50 are arranged in a predetermined first arrangement pattern with respect to their mutual circumferential angular distance, the second group of guide ribs 50 being arranged in a second arrangement pattern with respect to their mutual circumferential angular distance, which is a reflection of the first arrangement pattern at the
Symmetrieachse Y darstellt Symmetry axis Y represents
Gemäß der in Fig.2 gezeigten Ausgestaltung der Erfindung ist das vorbestimmte erste Anordnungsmuster der ersten Gruppe von Leitrippen 50 definiert durch die Winkelmaße: a=27 Grad, b=1 ,8 Grad, c=34,2 Grad und d=59,4 Grad. Das zweite Anordnungsmuster der zweiten Gruppe von Leitrippen 50 ist definiert durch die Winkelmaße: a'=27 Grad, b'=1 ,8 Grad, c'=34,2 Grad und d'=59,4 Grad. According to the embodiment of the invention shown in FIG. 2, the predetermined first arrangement pattern of the first group of guide ribs 50 is defined by the angular dimensions: a = 27 degrees, b = 1, 8 degrees, c = 34.2 degrees and d = 59.4 Degree. The second arrangement pattern of the second group of guide ribs 50 is defined by the angular dimensions: a '= 27 degrees, b' = 1, 8 degrees, c '= 34.2 degrees and d' = 59.4 degrees.
Mit anderen Worten ergibt sich gemäß Fig.2 in jeder Gruppe von Leitrippen 50 eine Kombination von Winkelabständen zwischen den Leitrippen 50 von In other words, according to Figure 2 results in each group of guide ribs 50, a combination of angular intervals between the guide ribs 50 of
28,2 Grad, 32,4 Grad und 25,2 Grad, wobei die beiden Gruppen von Leitrippen 50 einen Winkelabstand von 61 ,2 Grad (in Fig.2 unten) bzw. 126 Grad (in Fig.2 oben) haben. 28.2 degrees, 32.4 degrees and 25.2 degrees, wherein the two groups of guide ribs 50 have an angular spacing of 61, 2 degrees (in Fig.2 below) and 126 degrees (in Fig.2 above).
Gemäß nicht dargestellten anderen Ausführungsformen der Erfindung könnten das erste und das zweite Anordnungsmuster auch vollkommen unterschiedlich sein. Die spezielle Realisierung des ersten und zweiten Anordnungsmusters bzw. des jeweiligen Winkelabstands der Leitrippen 50 kann von der jeweiligen z B. According to other embodiments of the invention, not shown, the first and second arrangement patterns could also be completely different his. The specific realization of the first and second arrangement pattern or of the respective angular spacing of the guide ribs 50 can be different from the respective example B.
dimensionalen und/oder förmlichen Ausgestaltung der Gasturbine 1 abhängen und damit gemäß den dort auftretenden speziellen Strömungsverhältnissen anpassbar sein. depend dimensional and / or formal design of the gas turbine 1 and thus be customizable according to the specific flow conditions occurring there.
In Fig.4 ist in zwei Querschnittsansichten ein Vergleich der Luftströmungs- und Druckverteilungen in dem Brennkammergehäuse 10 gezeigt, wobei das 4, a comparison of the air flow and pressure distributions in the combustion chamber housing 10 is shown in two cross-sectional views, wherein the
Brennkammergehäuse gemäß der in Fig.4 oberen Darstellung ohne Leitrippen 50 und das Brennkammergehäuse gemäß der in Fig.4 unteren Darstellung gemäß der Erfindung mit Leitrippen 50 ausgeführt ist. Combustion chamber housing according to the upper view in Figure 4 without guide fins 50 and the combustion chamber housing according to the bottom in Figure 4 representation according to the invention with guide ribs 50 is executed.
Wie aus der oberen Darstellung von Fig 4 ersichtlich, stellen sich ohne Leitrippen 50 im Betrieb der Gasturbine 1 aufgrund der umfangsmäßigen Umströmung des Flammrohrs 20 in dem Zwischenraum 40 inhomogene Luftströmungs- und As can be seen from the upper illustration of FIG. 4, without guide ribs 50 in operation of the gas turbine 1 due to the circumferential flow around the flame tube 20 in the intermediate space 40, inhomogeneous air flow and flow
Druckverhältnisse ein. Pressure conditions.
Wie aus der unteren Darstellung von Fig.4 ersichtlich, stellen sich mit den quer zur Umströmungsrichtung der einströmenden Luft stehenden Leitrippen 50 im Betrieb der Gasturbine 1 aufgrund des damit erzielten Unterbindens der umfangsmäßigen Umströmung des Flammrohrs 20 in dem Zwischenraum 40 im Wesentlichen homogene Luftströmungs- und Druckverhältnisse ein, womit eine gleichmäßige Verteilung der einströmenden Luft um das Flammrohr 20 erreicht und die Kühlung des Flammrohres 20 verbessert wird. Zusätzlich wird die Luft nach der Umlenkung von radialer auf axiale Strömung kanalförmig geführt, so dass die Zuströmung zur nachfolgenden Verbrennungszone homogen erfolgt Bezugszeichenliste As can be seen from the lower illustration of FIG. 4, the guide ribs 50 which are transverse to the direction of flow of the incoming air during operation of the gas turbine 1 produce substantially homogeneous airflow and flow conditions in the intermediate space 40 due to the resulting obstruction of the circumferential flow around the flame tube 20 Pressure conditions, whereby a uniform distribution of the incoming air reaches around the flame tube 20 and the cooling of the flame tube 20 is improved. In addition, the air is channel-shaped after the deflection from radial to axial flow, so that the inflow to the subsequent combustion zone is homogeneous LIST OF REFERENCE NUMBERS
1 Gasturbine 1 gas turbine
10 Brennkammergehäuse 20 Flammrohr  10 combustion chamber housing 20 flame tube
30 Ummantelungsrohr 30 sheath tube
31 Durchgangsöffnungen31 passage openings
40 Zwischenraum 40 space
41 Längskanal  41 longitudinal channel
50 Leitrippe 50 leader rib
S Spalt  S cleft
LR Längsrichtung  LR longitudinal direction
Y Symmetrieachse a, b, c, d Winkelmaß  Y symmetry axis a, b, c, d angular dimension
a', b', c', d' Winkelmaß a ', b', c ', d' angle

Claims

Patentansprüche claims
1. Brennkammergehäuse (10) mit: 1. combustion chamber housing (10) with:
einem Flammrohr (20). und  a flame tube (20). and
einem Ummantelungsrohr (30), welches das Flammrohr (20) umgibt und welches in seiner Wandung eine Mehrzahl von Durchgangsöffnungen (31) hat. über die außen auf das Ummantelungsrohr (30) aufströmende Luft radial in einen zwischen dem Ummantelungsrohr (30) und dem Flammrohr (20) gebildeten Zwischenraum (40) eindringen kann.  a jacket tube (30) which surrounds the flame tube (20) and which has in its wall a plurality of passage openings (31). via the outside on the sheath tube (30) flowing air can penetrate radially into a between the sheath tube (30) and the flame tube (20) formed intermediate space (40).
gekennzeichnet durch eine Mehrzahl von in dem Zwischenraum (40) umfänglich der beiden Rohre verteilt angeordneten Leitrippen (50). die sich jeweils radial zwischen Ummantelungsrohr (30) und Flammrohr (20) sowie parallel zu einer Längsrichtung (LR) von Ummantelungsrohr (30) und Flammrohr (20) erstrecken, so dass der Zwischenraum (40) durch die Leitrippen (50) in mehrere Längskanäle (41) unterteilt ist  characterized by a plurality of distributed in the intermediate space (40) circumferentially of the two tubes distributed guide ribs (50). each extending radially between the sheath tube (30) and the flame tube (20) and parallel to a longitudinal direction (LR) of sheath tube (30) and flame tube (20), so that the intermediate space (40) through the guide ribs (50) in a plurality of longitudinal channels (41) is divided
Brennkammergehäuse (10) gemäß Anspruch 1 , wobei die Lertrippen (50) Ummantelungsrohr (30) angebracht sind. A combustion chamber housing (10) according to claim 1, wherein the gutter ribs (50) shroud tube (30) are mounted.
3. Brennkammergehäuse (10) gemäß Anspruch 2. wobei sich jede Leitrippe (50) radial so erstreckt, dass zwischen Leitrippe (50) und Flammrohr (20) ein Spalt (S) gebildet ist. 3. combustion chamber housing (10) according to claim 2 wherein each guide rib (50) extends radially so that between the guide rib (50) and the flame tube (20), a gap (S) is formed.
4. Brennkammergehäuse ( 10) gemäß einem der Ansprüche 1 bis 3, wobei die Leitrippen (50) jeweils streifenförmig ausgebildet sind. 4. combustion chamber housing (10) according to one of claims 1 to 3, wherein the guide ribs (50) are each formed strip-shaped.
Brennkammergehäuse (10) gemäß Anspruch 4, wobei die Leitrippen (50) Dickenabmessung von 3 mm aufweisen. A combustion chamber housing (10) according to claim 4, wherein the guide ribs (50) have a thickness of 3 mm.
6. Brennkammergehäuse (10) gemäß einem der Ansprüche 1 bis 5, wobei die Leitrippen (50) und die in der Wandung des Ummantelungsrohrs (30) 6. combustion chamber housing (10) according to one of claims 1 to 5, wherein the guide ribs (50) and in the wall of the sheath tube (30)
ausgebildeten Durchgangsöffnungen (31) so angeordnet sind, dass die Leitrippen (50) keine der Durchgangsöffnungen (31) verschließen. formed through holes (31) are arranged so that the guide ribs (50) do not close any of the through holes (31).
7 Brennkammergehäuse (10) gemäß einem der Ansprüche 1 bis 6, wobei die Mehrzahl von Leitrippen (50) von genau acht identischen Leitrippen (50) gebildet ist. 7. The combustion chamber housing according to claim 1, wherein the plurality of guide ribs are formed by exactly eight identical guide ribs.
8 Brennkammergehäuse (10) gemäß einem der Ansprüche 1 bis 7, wobei die Leitrippen (50) mit unterschiedlichem umfänglichen Winkelabstand voneinander in dem Zwischenraum (40) angeordnet sind. A combustion chamber housing (10) according to any one of claims 1 to 7, wherein the guide ribs (50) are arranged at different circumferentially spaced intervals in the space (40).
9. Brennkammergehäuse (10) gemäß einem der Ansprüche 1 bis 8, wobei die Leitrippen (50) eine erste Gruppe von Leitrippen (50) und eine zweite Gruppe von Leitrippen (50) aufweisen, wobei die erste Gruppe von Leitrippen (50) bezüglich ihres gegenseitigen umfänglichen Winkelabstands in einem vorbestimmten ersten Anordnungsmuster angeordnet sind, und wobei die zweite Gruppe von Leitrippen (50) bezüglich ihres gegenseitigen umfänglichen Winkelabstands in einem zweiten Anordnungsmuster angeordnet sind, welches eine Spiegelung des ersten 9. combustion chamber housing (10) according to one of claims 1 to 8, wherein the guide ribs (50) have a first group of guide ribs (50) and a second group of guide ribs (50), wherein the first group of guide ribs (50) with respect Mutual circumferential angular distance are arranged in a predetermined first arrangement pattern, and wherein the second group of guide ribs (50) are arranged with respect to their mutual circumferential angular distance in a second arrangement pattern, which is a reflection of the first
Anordnungsmusters an einer Symmetrieachse (Y) des Flammrohrs (20) darstellt. Arrangement pattern on an axis of symmetry (Y) of the flame tube (20) represents.
10 Gasturbine (1) mit einem Brennkammergehäuse (10) gemäß einem der Ansprüche 1 bis 9. 10 gas turbine (1) with a combustion chamber housing (10) according to one of claims 1 to 9.
EP12717246.8A 2011-04-18 2012-04-16 Combustion chamber housing and gas turbine equipped therewith Active EP2699848B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011007562A DE102011007562A1 (en) 2011-04-18 2011-04-18 Combustor housing and thus equipped gas turbine
PCT/EP2012/056878 WO2012143318A1 (en) 2011-04-18 2012-04-16 Combustion chamber housing and gas turbine equipped therewith

Publications (2)

Publication Number Publication Date
EP2699848A1 true EP2699848A1 (en) 2014-02-26
EP2699848B1 EP2699848B1 (en) 2015-06-10

Family

ID=46017823

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12717246.8A Active EP2699848B1 (en) 2011-04-18 2012-04-16 Combustion chamber housing and gas turbine equipped therewith

Country Status (7)

Country Link
US (1) US20140144138A1 (en)
EP (1) EP2699848B1 (en)
JP (1) JP5678232B2 (en)
CA (1) CA2833464A1 (en)
DE (1) DE102011007562A1 (en)
RU (1) RU2544400C1 (en)
WO (1) WO2012143318A1 (en)

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE709065C (en) * 1935-07-17 1941-08-07 Rene Alexandre Arthur Couzinet Feeding device for gas turbines
DE1004212B (en) 1953-11-07 1957-03-14 Westfalenhuette Ag Process for the heat treatment of reinforcing steel
US3915619A (en) * 1972-03-27 1975-10-28 Phillips Petroleum Co Gas turbine combustors and method of operation
GB1550368A (en) * 1975-07-16 1979-08-15 Rolls Royce Laminated materials
US4414816A (en) * 1980-04-02 1983-11-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Combustor liner construction
GB2087065B (en) * 1980-11-08 1984-11-07 Rolls Royce Wall structure for a combustion chamber
JPS62118958U (en) * 1986-01-16 1987-07-28
US5337568A (en) * 1993-04-05 1994-08-16 General Electric Company Micro-grooved heat transfer wall
DE4443864A1 (en) * 1994-12-09 1996-06-13 Abb Management Ag Cooled wall part
US5724816A (en) * 1996-04-10 1998-03-10 General Electric Company Combustor for a gas turbine with cooling structure
RU2138661C1 (en) * 1996-05-22 1999-09-27 Акционерное общество "Авиадвигатель" Gas turbine engine operating on cryogenic fuel
JPH1082527A (en) * 1996-09-05 1998-03-31 Toshiba Corp Gas turbine combustor
JP2002162036A (en) * 2000-11-22 2002-06-07 Mitsubishi Heavy Ind Ltd Combustor
WO2002088601A1 (en) * 2001-04-27 2002-11-07 Siemens Aktiengesellschaft Combustion chamber, in particular of a gas turbine
EP1288574A1 (en) * 2001-09-03 2003-03-05 Siemens Aktiengesellschaft Combustion chamber arrangement
RU36724U1 (en) * 2003-08-14 2004-03-20 Государственное предприятие Запорожское машиностроительное конструкторское бюро "Прогресс" им. акад. А.Г. Ивченко FRONT DEVICE OF COMBUSTION CHAMBER OF A GAS TURBINE ENGINE
DE102004016462A1 (en) * 2004-03-31 2005-11-24 Alstom Technology Ltd Coolable wall structure for especially gas turbine has cooling medium passing through passages formed in core and parallel to one another and parallel to inner and outer shells
RU2280814C1 (en) * 2004-12-27 2006-07-27 Акционерное общество открытого типа Авиамоторный научно-технический комплекс "Союз" Ring combustion chamber for gas-turbine engine
DE102006042124B4 (en) 2006-09-07 2010-04-22 Man Turbo Ag Gas turbine combustor
DE102007018061A1 (en) * 2007-04-17 2008-10-23 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber wall
DE102009035550A1 (en) * 2009-07-31 2011-02-03 Man Diesel & Turbo Se Gas turbine combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2012143318A1 *

Also Published As

Publication number Publication date
CA2833464A1 (en) 2012-10-26
RU2544400C1 (en) 2015-03-20
WO2012143318A1 (en) 2012-10-26
EP2699848B1 (en) 2015-06-10
DE102011007562A1 (en) 2012-10-18
JP5678232B2 (en) 2015-02-25
JP2014511991A (en) 2014-05-19
US20140144138A1 (en) 2014-05-29

Similar Documents

Publication Publication Date Title
DE102005025823B4 (en) Method and device for cooling a combustion chamber lining and a transition part of a gas turbine
EP0597138B1 (en) Combustion chamber for gas turbine
CH702825B1 (en) Turbine combustor insert assembly.
EP2340397B1 (en) Burner insert for a gas turbine combustion chamber and gas turbine
DE102008022669A1 (en) Fuel nozzle and method for its production
DE102014103083A1 (en) System and method for air conditioning at pipe level
DE102008055596A1 (en) Integrated inlet flow conditioner of a fuel nozzle
EP1865259A2 (en) Gas-turbine combustion chamber wall for a lean-burning gas-turbine combustion chamber
DE102010060283A1 (en) Fuel nozzle assembly for a gas turbine and method for assembling the same
EP3132202B1 (en) Bypass heat shield element
EP3004743B1 (en) Burner for a gas turbine and method for reducing thermo-acoustic oscillations in a gas turbine
DE102012100368A1 (en) Combustor nozzle and method of making the combustion chamber nozzle
DE112009000822T5 (en) Burner component and method of manufacture
EP2527743B1 (en) Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber
CH707842A2 (en) A method and apparatus for improving the heat transfer in the turbine sections of gas turbines.
EP2808611B1 (en) Injector for introducing a fuel-air mixture into a combustion chamber
WO2012113553A1 (en) Gas turbine combustion chamber
WO2012016748A2 (en) Gas turbine combustion chamber
EP3143335B1 (en) Burner for a combustion engine and combustion engine
EP2409086B1 (en) Burner assembly for a gas turbine
EP2459934B1 (en) Gas turbine combustion chamber
DE102013108599A1 (en) The combustor liner cooling assembly
DE102013112162A1 (en) Mikromischerdüse
EP2699848B1 (en) Combustion chamber housing and gas turbine equipped therewith
DE102022210198A1 (en) Transition piece, combustor and gas turbine engine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20131118

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502012003419

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F23R0003040000

Ipc: F23M0009020000

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/44 20060101ALI20150105BHEP

Ipc: F23M 9/02 20060101AFI20150105BHEP

Ipc: F23R 3/42 20060101ALI20150105BHEP

Ipc: F23R 3/06 20060101ALI20150105BHEP

Ipc: F23R 3/00 20060101ALI20150105BHEP

INTG Intention to grant announced

Effective date: 20150210

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 731077

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502012003419

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150910

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20150610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150910

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150911

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151010

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20151012

Ref country code: RO

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150610

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502012003419

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

26N No opposition filed

Effective date: 20160311

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160430

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160416

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161230

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160430

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160502

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160416

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20120416

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 731077

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170416

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170416

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150610

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502012003419

Country of ref document: DE

Owner name: MAN ENERGY SOLUTIONS SE, DE

Free format text: FORMER OWNER: MAN DIESEL & TURBO SE, 86153 AUGSBURG, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20220620

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230419

Year of fee payment: 12