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EP1391583A1 - Air cooled transition duct - Google Patents

Air cooled transition duct Download PDF

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Publication number
EP1391583A1
EP1391583A1 EP03015750A EP03015750A EP1391583A1 EP 1391583 A1 EP1391583 A1 EP 1391583A1 EP 03015750 A EP03015750 A EP 03015750A EP 03015750 A EP03015750 A EP 03015750A EP 1391583 A1 EP1391583 A1 EP 1391583A1
Authority
EP
European Patent Office
Prior art keywords
gas
cooling air
ribs
ring channel
flow channel
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
EP03015750A
Other languages
German (de)
French (fr)
Other versions
EP1391583B1 (en
Inventor
Hans-O. Dr. Jeske
Klaus Mohr
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 Turbomaschinen AG
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 Turbomaschinen AG filed Critical MAN Turbomaschinen AG
Publication of EP1391583A1 publication Critical patent/EP1391583A1/en
Application granted granted Critical
Publication of EP1391583B1 publication Critical patent/EP1391583B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a hot gas leading gas collector with the features of the preamble of claim 1.
  • a generic, two-armed, also called downpipe Gas collecting tube is known from DE 198 15 473 A1. Due to the special form of the inlet connection of this gas collection tube in the outlet cross section formed by the gas ring channel the middle areas much more thermally stressed than the upper and the lower area.
  • the gas ring channel of the gas collecting tube is cooled insofar that Cooling air is guided outside of the gas ring channel along. These Cooling air is taken from the compressor of the gas turbine plant. At the edges of the gas ring channel are provided two annular flanges, with slots for the passage of cooling air into the Flow channel of the gas turbine are provided. At one of the DE 100 32 454 A1 known gas collection tube are the cross sections the slots over the circumference of the annular flange so unevenly distributed, that at the more thermally loaded Areas of the gas collection tube a larger amount of cooling air is passed along as less thermally strong burdened areas. This is caused by an uneven Cooling air quantity uniform cooling of the gas ring channel of Gas collection tube reached.
  • the invention is based on the object, the generic To design gas collection tube such that the DE 100 32 454 A1 known leadership of the cooling air by other means simultaneous intensification of the cooling is achieved.
  • the ribs are so misplaced that they are directed to the gas collection pipe Redirect cooling air flow and preferably to the middle, at strongest thermally loaded area of the gas collection pipe judge.
  • the surface of the more thermally stressed area increases, where by a better heat dissipation is achieved.
  • Benefits consist in a reduction of the local, life-limiting material temperature, in one Equalization of the temperature distribution, in a reduction of temperature stresses, in an improvement of the temperature and Corrosion resistance and in an increase of Life of the gas collection tube.
  • Another advantage is that no increased Cooling air required.
  • the hot zones are supplied with additional cooling air. This additional Cooling air is usually not available, or they leads to a reduction in the efficiency of the machine.
  • a gas turbine plant is shown in this regard, as it is necessary for the understanding of the invention.
  • the Gas turbine plant is known per se and consists of a Compressor, a gas turbine and in the present case of two external combustion chambers 9 in V arrangement. In the presentation 4, only one of the combustion chambers 9 can be seen.
  • the Gas turbine includes a turbine runner 10, the rotor blades 12 carries, which is within the annular flow channel 13th the gas turbine are located. At the flow channel 13 closes a serving as a gas collecting gas ring channel 4 at.
  • the Compressor of the gas turbine plant is in Fig. 4, only the Recognize compressor blade 11 of the compressor rotor.
  • the connection between the two combustion chambers 9 of Gas turbine plant and the flow channel 13 of the gas turbine takes place via a hot gas leading two-arm gas manifold 1, which is shown in more detail in Figs. 1 to 3.
  • the gas collection pipe 1 is provided with two inlet ports 2, each to the Gas outlet of one of the combustion chambers 9 are connected.
  • the Inlet 2 open through a bend 3 of 90 ° in one serving as a gas collecting gas ring channel 4 in the lower part of the Gas collecting pipe 1 a.
  • the gas collecting pipe 1 is provided with an outer Ring flange 5 and an inner annular flange 6 is provided, the corresponding mating flanges of the housing of the gas turbine be connected.
  • the compressed hot gas flows out of the Combustion chambers 9 through the inlet 2 of the gas collection pipe. 1 and is brought together and collected in the gas ring channel 4, before flowing into the flow channel 13 and the turbine runner 10 offset with the blades 12 in rotation.
  • the Gasringkanal 4 of the gas collection tube 1 by the zoomed Hot gas unevenly thermally loaded Due to the formation of the entrance 2 is the Gasringkanal 4 of the gas collection tube 1 by the zoomed Hot gas unevenly thermally loaded.
  • the middle areas, the 3 o'clock and the 9 o'clock position correspond, more heavily loaded than the upper and the lower Area of the gas ring channel 4 corresponding to the 6 o'clock and the 12 o'clock position.
  • the entire gas collection pipe 1 is outside by compressor air convectively cooled, the compressor of the gas turbine plant is removed.
  • This cooling air is outside of the bend 3 and then guided along the gas ring channel 4 along.
  • To this Purpose are in the outer and inner annular flange 5, 6, the as rings protrude into the flow path of the cooling air, slots 7 or other openings attached. Through these slots 7 the cooling air flows off.
  • Driving force for the flow of Cooling air is a pressure difference that extends to both sides of the slotted annular flanges 5, 6 builds.
  • the ribs 8 extend in the radial direction over the near-wall area.
  • the height of the ribs 8 depends on the size of the Gas turbine off. At a height of the gas ring channel 4 of about 70 mm, the height of the ribs 8 is about 5 to 10 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Sampling And Sample Adjustment (AREA)

Abstract

The gas collection pipe (1) has two circular inlets (2) receiving hot gas from two separate combustion chambers. The inlets blend, via a curved portion (3), into an annular passage (4) which has an annular outlet to the rim of the turbine wheel. There are curved reinforcement ribs (8) on the sides of the annular passage remote from the turbine. Slits (7) act as inlets for cooling air and there is a coupling flange (6).

Description

Die Erfindung betrifft ein Heißgas führendes Gassammelrohr mit den Merkmalen des Oberbegriffes des Anspruches 1.The invention relates to a hot gas leading gas collector with the features of the preamble of claim 1.

Ein gattungsgemäßes, zweiarmiges, auch Hosenrohr genanntes Gassammelrohr ist aus der DE 198 15 473 A1 bekannt. Aufgrund der besonderen Form der Eintrittsstutzen dieses Gassammelrohres sind in dessen durch den Gasringkanal gebildeten Austrittsquerschnitt die mittleren Bereiche wesentlich stärker thermisch belastet als der obere und der untere Bereich.A generic, two-armed, also called downpipe Gas collecting tube is known from DE 198 15 473 A1. Due to the special form of the inlet connection of this gas collection tube in the outlet cross section formed by the gas ring channel the middle areas much more thermally stressed than the upper and the lower area.

Gekühlt wird der Gasringkanal des Gassammelrohres insofern, dass Kühlluft außen an dem Gasringkanal entlang geführt wird. Diese Kühlluft wird dem Kompressor der Gasturbinenanlage entnommen. An den Kanten des Gasringkanals sind zwei Ringflansche vorgesehen, die mit Schlitzen für den Durchtritt der Kühlluft in den Strömungskanal der Gasturbine versehen sind. Bei einem aus der DE 100 32 454 A1 bekannten Gassammelrohr sind die Querschnitte der Schlitze über den Umfang des Ringflansches derart ungleichmäßig verteilt, dass an den stärker thermisch belasteten Bereichen des Gassammelrohres eine größere Menge an Kühlluft entlang geführt wird als an den weniger thermisch stark belasteten Bereichen. Dadurch wird durch eine ungleichmäßige Kühlluftmenge eine gleichmäßige Kühlung des Gasringkanals des Gassammelrohres erreicht.The gas ring channel of the gas collecting tube is cooled insofar that Cooling air is guided outside of the gas ring channel along. These Cooling air is taken from the compressor of the gas turbine plant. At the edges of the gas ring channel are provided two annular flanges, with slots for the passage of cooling air into the Flow channel of the gas turbine are provided. At one of the DE 100 32 454 A1 known gas collection tube are the cross sections the slots over the circumference of the annular flange so unevenly distributed, that at the more thermally loaded Areas of the gas collection tube a larger amount of cooling air is passed along as less thermally strong burdened areas. This is caused by an uneven Cooling air quantity uniform cooling of the gas ring channel of Gas collection tube reached.

Der Erfindung liegt die Aufgabe zugrunde, das gattungsgemäße Gassammelrohr derart zu gestalten, dass die aus der DE 100 32 454 A1 bekannte Führung der Kühlluft mit anderen Mitteln bei gleichzeitiger Intensivierung der Kühlung erreicht wird. The invention is based on the object, the generic To design gas collection tube such that the DE 100 32 454 A1 known leadership of the cooling air by other means simultaneous intensification of the cooling is achieved.

Die Aufgabe wird bei einem gattungsgemäßen Gassammelrohr erfindungsgemäß durch die kennzeichnenden Merkmale des Anspruches 1 gelöst. Vorteilhafte Ausgestaltung der Erfindung sind Gegenstand der Unteransprüche.The task is in a generic gas collection tube According to the invention by the characterizing features of Claim 1 solved. Advantageous embodiment of the invention are the subject of the dependent claims.

Bei dem erfindungsgemäßen Gassammelrohr sind die Rippen so verlegt, dass sie den auf das Gassammelrohr gerichteten Kühlluftstrom umlenken und bevorzugt auf den mittleren, am stärksten thermisch belasteten Bereich des Gassammelrohr richten. Darüber hinaus wird durch die Rippen die Oberfläche des stärker thermisch belasteten Bereiches vergrößert, wo durch eine bessere Wärmeabfuhr erreicht wird.In the gas collecting pipe according to the invention, the ribs are so misplaced that they are directed to the gas collection pipe Redirect cooling air flow and preferably to the middle, at strongest thermally loaded area of the gas collection pipe judge. In addition, by the ribs the surface of the more thermally stressed area increases, where by a better heat dissipation is achieved.

Wie aus der DE 100 32 454 A1 bekannt ist, wird bei der Kühlung des Gassammelrohres die Kühlluftmenge insgesamt nicht erhöht. Es wird lediglich die Kühlluft, die normalerweise Bereiche kühlt, die nur eine geringe Temperaturbelastung haben, zu den Bereichen geführt, die temperaturmäßig höher belastet sind. Dadurch steigt die Materialtemperatur des Austrittsquerschnittes in den kalten Zonen. Jedoch fallen die Temperaturen in den beiden heißen Zonen, so dass sich auf dem Umfang betrachtet ein nahezu gleichmäßiges Temperaturprofil ergibt.As is known from DE 100 32 454 A1, is used in the cooling of the gas collection tube does not increase the total amount of cooling air. It only the cooling air that normally cools areas, which only have a low temperature load to the areas led, which are higher in temperature. This increases the material temperature of the outlet cross section in the cold Zones. However, the temperatures fall in the two hot Zones, so that on the perimeter considered a nearly uniform temperature profile results.

Die sich durch die erfindungsgemäßen Maßnahmen ergebende Vorteile bestehen in einer Reduzierung der lokalen, lebensdauerbegrenzenden Materialtemperatur, in einer Vergleichmäßigung der Temperaturverteilung, in einer Reduzierung von Temperaturspannungen, in einer Verbesserung der Temperaturund Korrosionsbeständigkeit und in einer Erhöhung der Lebensdauer des Gassammelrohres.The resulting from the inventive measures Benefits consist in a reduction of the local, life-limiting material temperature, in one Equalization of the temperature distribution, in a reduction of temperature stresses, in an improvement of the temperature and Corrosion resistance and in an increase of Life of the gas collection tube.

Ein weiterer Vorteil liegt darin, dass kein erhöhter Kühlluftbedarf erforderlich. Bei den bisher bekannten und angewendeten Methoden zur Begegnung von Temperaturspitzen in temperaturmäßig hochbelasteten Bauteilen wird in der Regel den heißen Zonen zusätzliche Kühlluft zugeführt. Diese zusätzliche Kühlluft steht aber in der Regel nicht zur Verfügung, oder sie führt zu einer Reduzierung des Wirkungsgrades der Maschine.Another advantage is that no increased Cooling air required. In the previously known and applied methods for meeting temperature peaks in Temperaturmäßig highly loaded components is usually the hot zones are supplied with additional cooling air. This additional Cooling air is usually not available, or they leads to a reduction in the efficiency of the machine.

Ein Ausführungsbeispiel der Erfindung ist in der Zeichnung dargestellt und wird im Folgenden näher erläutert. Es zeigen:

Fig. 1
in perspektivischer Ansicht ein Gassammelrohr nach der Erfindung schräg von oben von der Anströmseite her gesehen,
Fig. 2
in perspektivischer Ansicht ein Gassammelrohr nach der Erfindung von der Anströmseite her gesehen,
Fig. 3
in perspektivischer Ansicht ein Gassammelrohr nach der Erfindung schräg von der Seite aus gesehen und
Fig. 4
einen Ausschnitt aus einer Gasturbinenanlage als Halbschnitt durch den Übergang zwischen dem Verdichterteil und dem Turbinenteil der Gasturbinenanlage.
An embodiment of the invention is illustrated in the drawing and will be explained in more detail below. Show it:
Fig. 1
in a perspective view of a gas manifold according to the invention seen obliquely from above from the upstream side,
Fig. 2
in a perspective view of a gas manifold according to the invention seen from the upstream side,
Fig. 3
in a perspective view of a gas manifold according to the invention seen obliquely from the side and
Fig. 4
a detail of a gas turbine plant as a half-section through the transition between the compressor part and the turbine part of the gas turbine plant.

In der Fig. 4 ist eine Gasturbinenanlage insoweit gezeigt, wie es für das Verständnis der Erfindung notwendig ist. Die Gasturbinenanlage ist an sich bekannt und besteht aus einem Verdichter, einer Gasturbine und im vorliegenden Fall aus zwei außenliegenden Brennkammern 9 in V-Anordnung. In der Darstellung der Fig. 4 ist nur eine der Brennkammern 9 zu erkennen. Die Gasturbine enthält einen Turbinenläufer 10, der Laufschaufeln 12 trägt, die sich innerhalb des ringförmigen Strömungskanales 13 der Gasturbine befinden. An den Strömungskanal 13 schließt sich ein als Gassammelraum dienender Gasringkanal 4 an. Von dem Verdichter der Gasturbinenanlage ist in Fig. 4 lediglich die Verdichterbeschaufelung 11 des Verdichterrotors zu erkennen.In Fig. 4, a gas turbine plant is shown in this regard, as it is necessary for the understanding of the invention. The Gas turbine plant is known per se and consists of a Compressor, a gas turbine and in the present case of two external combustion chambers 9 in V arrangement. In the presentation 4, only one of the combustion chambers 9 can be seen. The Gas turbine includes a turbine runner 10, the rotor blades 12 carries, which is within the annular flow channel 13th the gas turbine are located. At the flow channel 13 closes a serving as a gas collecting gas ring channel 4 at. Of the Compressor of the gas turbine plant is in Fig. 4, only the Recognize compressor blade 11 of the compressor rotor.

Die Verbindung zwischen den beiden Brennkammern 9 der Gasturbinenanlage und dem Strömungskanal 13 der Gasturbine erfolgt über ein Heißgas führendes zweiarmiges Gassammelrohr 1, das in den Fig. 1 bis 3 näher dargestellt ist. Das Gassammelrohr 1 ist mit zwei Eintrittsstutzen 2 versehen, die jeweils an den Gasaustritt einer der Brennkammern 9 angeschlossen sind. Die Eintrittsstutzen 2 münden über eine Krümmung 3 von 90° in einen als Gassammelraum dienenden Gasringkanal 4 im unteren Teil des Gassammelrohres 1 ein. Das Gassammelrohr 1 ist mit einem äußeren Ringflansch 5 und einem inneren Ringflansch 6 versehen, die an entsprechende Gegenflansche des Gehäuses der Gasturbine angeschlossen werden. Das komprimierte Heißgas strömt aus den Brennkammern 9 durch die Eintrittssutzen 2 des Gassammelrohres 1 und wird in dem Gasringkanal 4 zusammengeführt und gesammelt, bevor es in den Strömungskanal 13 strömt und den Turbinenläufer 10 mit den Laufschaufeln 12 in Rotation versetzt.The connection between the two combustion chambers 9 of Gas turbine plant and the flow channel 13 of the gas turbine takes place via a hot gas leading two-arm gas manifold 1, which is shown in more detail in Figs. 1 to 3. The gas collection pipe 1 is provided with two inlet ports 2, each to the Gas outlet of one of the combustion chambers 9 are connected. The Inlet 2 open through a bend 3 of 90 ° in one serving as a gas collecting gas ring channel 4 in the lower part of the Gas collecting pipe 1 a. The gas collecting pipe 1 is provided with an outer Ring flange 5 and an inner annular flange 6 is provided, the corresponding mating flanges of the housing of the gas turbine be connected. The compressed hot gas flows out of the Combustion chambers 9 through the inlet 2 of the gas collection pipe. 1 and is brought together and collected in the gas ring channel 4, before flowing into the flow channel 13 and the turbine runner 10 offset with the blades 12 in rotation.

Aufgrund der Ausbildung der Eintrittssutzen 2 ist der Gasringkanal 4 des Gassammelrohres 1 durch das herangeführte Heißgas ungleichmäßig thermisch belastet. Dabei sind die mittleren Bereiche, die der 3-Uhr- und der 9-Uhr-Stellung entsprechen, stärker belastet als der obere und der untere Bereich des Gasringkanales 4 entsprechend der 6-Uhr- und der 12-Uhr-Stellung.Due to the formation of the entrance 2 is the Gasringkanal 4 of the gas collection tube 1 by the zoomed Hot gas unevenly thermally loaded. Here are the middle areas, the 3 o'clock and the 9 o'clock position correspond, more heavily loaded than the upper and the lower Area of the gas ring channel 4 corresponding to the 6 o'clock and the 12 o'clock position.

Das gesamte Gassammelrohr 1 wird durch Verdichterluft außen konvektiv gekühlt, die dem Verdichter der Gasturbinenanlage entnommen wird. Diese Kühlluft wird außen an der Krümmung 3 und anschließend an dem Gasringkanal 4 entlang geführt. Zu diesem Zweck sind in dem äußeren und dem inneren Ringflansch 5, 6, die als Ringe in den Strömungsweg der Kühlluft hineinragen, Schlitze 7 oder andere Öffnungen angebracht. Durch diese Schlitze 7 strömt die Kühlluft ab. Treibende Kraft für den Strom der Kühlluft ist eine Druckdifferenz, die sich zu beiden Seiten der geschlitzten Ringflansche 5, 6 aufbaut.The entire gas collection pipe 1 is outside by compressor air convectively cooled, the compressor of the gas turbine plant is removed. This cooling air is outside of the bend 3 and then guided along the gas ring channel 4 along. To this Purpose are in the outer and inner annular flange 5, 6, the as rings protrude into the flow path of the cooling air, slots 7 or other openings attached. Through these slots 7 the cooling air flows off. Driving force for the flow of Cooling air is a pressure difference that extends to both sides of the slotted annular flanges 5, 6 builds.

Zur Führung der Kühlluft sind auf der dem Eintrittsflansch der Gasturbine abgewandten Seite außen auf dem Gassammelrohr 1 im Bereich der Krümmung 3 mehrere Rippen 8 mit Abstand voneinander, beispielsweise durch Punktschweißung, angebracht. Diese Rippen 8 sind entlang der Krümmung 3 ausgehend von dem Übergangsbereich in die Eintrittsstutzen 2 bis in den mittleren Bereich des Gasringkanales 4 sowohl auf dessen Innen- als auch auf dessen Außenseite geführt. Die so angeordneten Rippen 8 leiten die mehr oder weniger gerichtet anströmende Kühlluft an die heißesten Stellen des Gassammelrohres 1, um diese besonders stark zu kühlen. Gleichzeitig wird durch die Rippen die zu kühlende Oberfläche vergrößert, wodurch die Kühlung noch intensiviert wird.To guide the cooling air are on the inlet flange of the Gas turbine side facing away from the outside on the gas manifold 1 in Range of curvature 3 multiple ribs 8 spaced from each other, by spot welding, for example. These ribs 8 are along the curve 3 starting from the transition region into the inlet 2 to the middle area of the Gasringkanales 4 both on its inside and on the Outside led. The thus arranged ribs 8 conduct the more or less directed incoming cooling air to the hottest Make the gas collection tube 1 to this particularly strong cool. At the same time by the ribs to be cooled Enlarged surface, whereby the cooling is intensified becomes.

Die Rippen 8 erstrecken sich in radialer Richtung über den wandnahen Bereich. Die Höhe der Rippen 8 hängt von der Größe der Gasturbine ab. Bei einer Höhe des Gasringkanales 4 von etwa 70 mm beträgt die Höhe der Rippen 8 etwa 5 bis 10 mm.The ribs 8 extend in the radial direction over the near-wall area. The height of the ribs 8 depends on the size of the Gas turbine off. At a height of the gas ring channel 4 of about 70 mm, the height of the ribs 8 is about 5 to 10 mm.

Claims (3)

Heißgas führendes Gassammelrohr zur Verbindung zwischen den Brennkammern (9) einer Gasturbinenanlage und dem Strömungskanal (13) der Gasturbine, wobei das Gassammelrohr (1) zwei Eintrittsstutzen (2) aufweist, die über eine Krümmung (3) axial in einen Gasringkanal (4) einmünden, der an den Strömungskanal (13) angeschlossen ist und wobei Kühlluft außen an der Krümmung (3) entlang geführt ist, dadurch gekennzeichnet, dass auf der dem Strömungskanal (13) abgewandten Seite außen auf dem Gassammelrohr (1) im Bereich der Krümmung (3) mehrere Rippen (8) mit Abstand voneinander angebracht sind.Hot gas leading gas collection pipe for connection between the combustion chambers (9) of a gas turbine plant and the flow channel (13) of the gas turbine, wherein the gas collection tube (1) has two inlet connections (2), which open via a bend (3) axially into a gas ring channel (4) which is connected to the flow channel (13) and wherein cooling air is guided externally along the curvature (3), characterized in that on the side facing away from the flow channel (13) on the outside of the gas collecting tube (1) in the region of the curvature (3 ) a plurality of ribs (8) are mounted at a distance from each other. Gassammelrohr nach Anspruch 1, dadurch gekennzeichnet, dass die Rippen (8) entlang der Krümmung (3) ausgehend von dem Übergangsbereich in die Eintrittsstutzen (2) bis in den mittleren Bereich des Gasringkanales (4) auf dessen Innenund Außenseite geführt sind.Gas collecting pipe according to claim 1, characterized in that the ribs (8) along the curvature (3), starting from the transition region in the inlet nozzle (2) to the central region of the gas ring channel (4) are guided on the inside and outside. Gassammelrohr nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Höhe der Rippen (8) etwa 10 % der Höhe des Gasringkanales (4) beträgt.Gas collecting pipe according to claim 1 or 2, characterized in that the height of the ribs (8) is about 10% of the height of the gas ring channel (4).
EP03015750A 2002-08-23 2003-07-10 Air cooled transition duct Expired - Lifetime EP1391583B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10239534 2002-08-23
DE10239534A DE10239534A1 (en) 2002-08-23 2002-08-23 Hot gas leading gas manifold

Publications (2)

Publication Number Publication Date
EP1391583A1 true EP1391583A1 (en) 2004-02-25
EP1391583B1 EP1391583B1 (en) 2008-03-05

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EP03015750A Expired - Lifetime EP1391583B1 (en) 2002-08-23 2003-07-10 Air cooled transition duct

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US (1) US6996992B2 (en)
EP (1) EP1391583B1 (en)
JP (1) JP2007046456A (en)
CN (1) CN1255623C (en)
AT (1) ATE388303T1 (en)
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DE (2) DE10239534A1 (en)

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USD818502S1 (en) * 2015-12-17 2018-05-22 General Electric Company Turbocharger transition section
USD814522S1 (en) * 2016-06-21 2018-04-03 General Electric Company Transition section for a turbocharged engine

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DE10239534A1 (en) 2004-04-22
JP2007046456A (en) 2007-02-22
US6996992B2 (en) 2006-02-14
US20040035116A1 (en) 2004-02-26
CN1255623C (en) 2006-05-10
EP1391583B1 (en) 2008-03-05
CA2424166C (en) 2008-09-09
ATE388303T1 (en) 2008-03-15
CN1477298A (en) 2004-02-25
DE50309297D1 (en) 2008-04-17
CA2424166A1 (en) 2004-02-23

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