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EP1391583B1 - Air cooled transition duct - Google Patents

Air cooled transition duct Download PDF

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Publication number
EP1391583B1
EP1391583B1 EP03015750A EP03015750A EP1391583B1 EP 1391583 B1 EP1391583 B1 EP 1391583B1 EP 03015750 A EP03015750 A EP 03015750A EP 03015750 A EP03015750 A EP 03015750A EP 1391583 B1 EP1391583 B1 EP 1391583B1
Authority
EP
European Patent Office
Prior art keywords
gas
cooling air
ribs
collecting pipe
ring 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.)
Expired - Lifetime
Application number
EP03015750A
Other languages
German (de)
French (fr)
Other versions
EP1391583A1 (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 Turbo AG
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Filing date
Publication date
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Publication of EP1391583A1 publication Critical patent/EP1391583A1/en
Application granted granted Critical
Publication of EP1391583B1 publication Critical patent/EP1391583B1/en
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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 collection tube having the features of the preamble of claim 1.
  • a generic, two-armed, also called gutter gas collection tube is from the DE 198 15 473 A1 known. Due to the special shape of the inlet connection of this gas collecting tube, the central regions are much more thermally stressed in its outlet cross-section formed by the gas-ring channel than the upper and the lower regions.
  • the gas ring channel of the gas collection tube is cooled insofar that cooling air is guided along the outside of the gas ring channel. This cooling air is taken from the compressor of the gas turbine plant. At the edges of the gas ring channel two annular flanges are provided which are provided with slots for the passage of the cooling air into the flow channel of the gas turbine.
  • the cross-sections of the slots over the circumference of the annular flange are distributed so unevenly that at the more thermally stressed areas of the gas collection tube a larger amount of cooling air is guided along than at the less thermally heavily loaded areas.
  • a uniform cooling of the gas ring channel of the gas collecting tube is achieved by an uneven amount of cooling air.
  • EP-A-0 123 101 an air-cooled reciprocating internal combustion engine is described, the cylinder head is equipped with cooling fins.
  • the attached cooling fins increase the cooling to be cooled Surface, but are not due to their arrangement for the flow of cooling air.
  • CH-A-599458 is described an air-cooled internal combustion engine whose cylinder and the exhaust manifold are provided with cooling fins.
  • the cooling fins provided serve - as in the internal combustion engine according to EP-A-0 123 101 - only the enlargement of the surface.
  • the cooling fins do not have the function to particularly cool certain areas of the exhaust manifold or the cylinder by the cooling air is directed thereto specifically. Rather, all ribs are the same, arranged in parallel and formed without special shape.
  • the invention has for its object to make the generic gas collection tube such that from the DE 100 32 454 A1 known guidance of the cooling air is achieved by other means with simultaneous intensification of the cooling at certain points.
  • the ribs are laid so that they deflect the cooling air flow directed onto the gas collecting pipe and preferably point to the central, most thermally stressed region of the gas collecting pipe.
  • the surface of the more thermally stressed area is increased by the ribs, whereby a better heat dissipation is achieved.
  • the total cooling air amount is not increased in the cooling of the gas collection tube. It is only the cooling air, which normally cools areas that have only a low temperature load, led to the areas that 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 viewed on the circumference results in a nearly uniform temperature profile.
  • the advantages resulting from the measures according to the invention consist in a reduction of the local, life-limiting material temperature, in an equalization of the temperature distribution, in a reduction of temperature stresses, in an improvement of the temperature and corrosion resistance and in an increase in the service life of the gas collection tube.
  • Another advantage is that no increased cooling air requirement is required.
  • additional cooling air is usually supplied.
  • this additional cooling air is usually not available, or it leads to a reduction in the efficiency of the machine.
  • the gas collecting pipe 1 is provided with two inlet ports 2, which are connected to the gas outlet of one of the combustion chambers 9, respectively.
  • the inlet nozzle 2 open via a bend 3 of 90 ° in a serving as a gas collecting gas ring channel 4 in the lower part of the gas collection pipe 1 a.
  • the gas manifold 1 is provided with an outer annular flange 5 and an inner annular flange 6, the corresponding mating flanges of the housing of the gas turbine can be connected.
  • the compressed hot gas flows out of the combustion chambers 9 through the inlet ports 2 of the gas manifold 1 and is brought together and collected in the gas ring passage 4 before flowing into the flow passage 13 and rotating the turbine runner 10 with the blades 12.
  • the entire gas collection pipe 1 is convectively cooled by compressor air outside, which is taken from the compressor of the gas turbine plant. This cooling air is passed outside the bend 3 and then along the gas ring channel 4 along.
  • compressor air is passed outside the bend 3 and then along the gas ring channel 4 along.
  • slots 7 or other openings are attached in the outer and inner annular flange 5, 6, which protrude as rings in the flow path of the cooling air. Through these slots 7, the cooling air flows.
  • the driving force for the flow of cooling air is a pressure difference, which builds up on both sides of the slotted annular flanges 5, 6.
  • a plurality of ribs 8 at a distance from each other, for example by spot welding attached. These ribs 8 are guided along the curvature 3, starting from the transition region into the inlet connection 2 to the middle region of the gas ring channel 4 both on its inside and on the outside thereof.
  • the thus arranged ribs 8 conduct the more or less directed inflowing cooling air to the hottest points of the gas collection tube 1 in order to cool them particularly strong. At the same time the surface to be cooled is increased by the ribs, whereby the cooling is intensified.
  • the ribs 8 extend in the radial direction over the region near the wall.
  • the height of the ribs 8 depends on the size of the gas turbine. With a width 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 collection tube having 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 gutter gas collection tube is from the DE 198 15 473 A1 known. Due to the special shape of the inlet connection of this gas collecting tube, the central regions are much more thermally stressed in its outlet cross-section formed by the gas-ring channel than the upper and the lower regions.

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.The gas ring channel of the gas collection tube is cooled insofar that cooling air is guided along the outside of the gas ring channel. This cooling air is taken from the compressor of the gas turbine plant. At the edges of the gas ring channel two annular flanges are provided which are provided with slots for the passage of the cooling air into the flow channel of the gas turbine.

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.At one of the DE 100 32 454 A1 known gas collection tube, the cross-sections of the slots over the circumference of the annular flange are distributed so unevenly that at the more thermally stressed areas of the gas collection tube a larger amount of cooling air is guided along than at the less thermally heavily loaded areas. As a result, a uniform cooling of the gas ring channel of the gas collecting tube is achieved by an uneven amount of cooling air.

In EP-A-O 123 101 ist eine luftgekühlte Hubkolbenbrennkraftmaschine beschrieben, deren Zylinderkopf mit Kühlrippen bestückt ist. Die angebrachten Kühlrippen vergrößern die zu kühlende Oberfläche, dienen aber aufgrund ihrer Anordnung nicht zur Strömungsführung der Kühlluft.In EP-A-0 123 101 an air-cooled reciprocating internal combustion engine is described, the cylinder head is equipped with cooling fins. The attached cooling fins increase the cooling to be cooled Surface, but are not due to their arrangement for the flow of cooling air.

In CH-A-599 458 ist ein luftgekühlter Verbrennungsmotor beschrieben, dessen Zylinder und dessen Auslasskrümmer mit Kühlrippen versehen sind. Die vorgesehenen Kühlrippen dienen - wie bei der Brennkraftmaschine gemäß EP - A -0 123 101 - lediglich der Vergrößerung der Oberfläche. Die Kühlrippen haben nicht die Funktion, bestimmte Bereiche des Abgaskrümmers oder des Zylinders besonders zu kühlen, indem die Kühlluft gezielt dorthin gelenkt wird. Vielmehr sind alle Rippen gleich, parallel angeordnet und ohne besondere Form ausgebildet.In CH-A-599458 is described an air-cooled internal combustion engine whose cylinder and the exhaust manifold are provided with cooling fins. The cooling fins provided serve - as in the internal combustion engine according to EP-A-0 123 101 - only the enlargement of the surface. The cooling fins do not have the function to particularly cool certain areas of the exhaust manifold or the cylinder by the cooling air is directed thereto specifically. Rather, all ribs are the same, arranged in parallel and formed without special shape.

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 an bestimmten Stellen erreicht wird.The invention has for its object to make the generic gas collection tube such that from the DE 100 32 454 A1 known guidance of the cooling air is achieved by other means with simultaneous intensification of the cooling at certain points.

Die Aufgabe wird bei einem gattungsgemäßen Gassammelrohr erfindungsgemäß durch die kennzeichnenden Merkmale des Anspruches 1 gelöst. Eine vorteilhafte Ausgestaltung der Erfindung ist Gegenstand des Unteranspruchs.The object is achieved according to the invention in a generic gas manifold by the characterizing features of claim 1. An advantageous embodiment of the invention is the subject of the subclaim.

Bei dem erfindungsgemäßen Gassammelrohr sind die Rippen so verlegt, dass diese den auf das Gassammelrohr gerichteten Kühlluftstrom umlenken und bevorzugt auf den mittleren, am stärksten thermisch belasteten Bereich des Gassammelrohrs richten. Darüber hinaus wird durch die Rippen die Oberfläche des stärker thermisch belasteten Bereiches vergrößert, wodurch eine bessere Wärmeabfuhr erreicht wird.In the gas collecting pipe according to the invention, the ribs are laid so that they deflect the cooling air flow directed onto the gas collecting pipe and preferably point to the central, most thermally stressed region of the gas collecting pipe. In addition, the surface of the more thermally stressed area is increased by the ribs, whereby 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 den Umfang betrachtet ein nahezu gleichmäßiges Temperaturprofil ergibt.Like from the DE 100 32 454 A1 is known, the total cooling air amount is not increased in the cooling of the gas collection tube. It is only the cooling air, which normally cools areas that have only a low temperature load, led to the areas that 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 viewed on the circumference results in a nearly uniform temperature profile.

Die sich durch die erfindungsgemäßen Maßnahmen ergebenden Vorteile bestehen in einer Reduzierung der lokalen, lebensdauerbegrenzenden Materialtemperatur, in einer Vergleichmäßigung der Temperaturverteilung, in einer Reduzierung von Temperaturspannungen, in einer Verbesserung der Temperatur-und Korrosionsbeständigkeit und in einer Erhöhung der Lebensdauer des Gassammelrohres.The advantages resulting from the measures according to the invention consist in a reduction of the local, life-limiting material temperature, in an equalization of the temperature distribution, in a reduction of temperature stresses, in an improvement of the temperature and corrosion resistance and in an increase in the service life of the gas collection tube.

Ein weiterer Vorteil liegt darin, dass kein erhöhter Kühlluftbedarf erforderlich ist. 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 requirement is required. In the previously known and applied methods for meeting temperature peaks in high-temperature components subjected to the hot zones additional cooling air is usually supplied. However, this additional cooling air is usually not available, or it 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 the Fig. 4 a gas turbine plant is shown insofar 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 of the Fig. 4 only one of the combustion chambers 9 can be seen. The gas turbine includes a turbine runner 10 carrying blades 12 located within the annular flow passage 13 of the gas turbine. The flow channel 13 is followed by a gas ring channel 4 serving as a gas collecting space. From the compressor of the gas turbine plant is in Fig. 4 only to recognize the 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 the gas turbine plant and the flow channel 13 of the gas turbine via a hot gas leading two-armed gas manifold 1, which in the Fig. 1 to 3 is shown in more detail. The gas collecting pipe 1 is provided with two inlet ports 2, which are connected to the gas outlet of one of the combustion chambers 9, respectively. The inlet nozzle 2 open via a bend 3 of 90 ° in a serving as a gas collecting gas ring channel 4 in the lower part of the gas collection pipe 1 a. The gas manifold 1 is provided with an outer annular flange 5 and an inner annular flange 6, the corresponding mating flanges of the housing of the gas turbine can be connected. The compressed hot gas flows out of the combustion chambers 9 through the inlet ports 2 of the gas manifold 1 and is brought together and collected in the gas ring passage 4 before flowing into the flow passage 13 and rotating the turbine runner 10 with the blades 12.

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 12-Uhr- und der 6-Uhr-Stellung.Due to the formation of the inlet nozzle 2 of the gas ring channel 4 of the gas collection tube 1 is unevenly thermally loaded by the supplied hot gas. The middle areas corresponding to the 3 o'clock and 9 o'clock positions are more heavily loaded than the upper and lower areas of the gas ring channel 4 corresponding to the 12 o'clock and the 6 o'clock positions.

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 convectively cooled by compressor air outside, which is taken from the compressor of the gas turbine plant. This cooling air is passed outside the bend 3 and then along the gas ring channel 4 along. For this purpose, in the outer and inner annular flange 5, 6, which protrude as rings in the flow path of the cooling air, slots 7 or other openings are attached. Through these slots 7, the cooling air flows. The driving force for the flow of cooling air is a pressure difference, which builds up on both sides of the slotted annular flanges 5, 6.

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 gerichtete 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 on the side facing away from the inlet flange of the gas turbine side outside on the gas manifold 1 in the region of the curvature 3 a plurality of ribs 8 at a distance from each other, for example by spot welding attached. These ribs 8 are guided along the curvature 3, starting from the transition region into the inlet connection 2 to the middle region of the gas ring channel 4 both on its inside and on the outside thereof. The thus arranged ribs 8 conduct the more or less directed inflowing cooling air to the hottest points of the gas collection tube 1 in order to cool them particularly strong. At the same time the surface to be cooled is increased by the ribs, whereby the cooling is intensified.

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 Breite 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 region near the wall. The height of the ribs 8 depends on the size of the gas turbine. With a width of the gas ring channel 4 of about 70 mm, the height of the ribs 8 is about 5 to 10 mm.

Claims (2)

  1. Gas collecting pipe, which conducts hot gas, for connection between combustion chambers (9) of a gas turbine installation and a flow channel (13) of the gas turbine, wherein the gas collecting pipe (1) has two inlet stub pipes (2) which axially open by way of an elbow (3) into a gas ring channel (4) connected with the flow channel (13) and wherein cooling air is led externally along the elbow (3), characterised in that several mutually spaced-apart ribs (8) guiding cooling air are formed externally on the gas collecting pipe (1) on the side, which is remote from the flow channel (13), in the region of the elbow (3), that the ribs (8) are led along the elbow (3), starting from the transition region to the inlet stub pipes (2), as far as the middle region of the gas ring channel (4) on the inner and outer side thereof and that the ribs (8) are arranged to conduct the cooling air to the hottest places of the gas collecting pipe (1).
  2. Gas collecting pipe according to claim 1, characterised in that the height of the ribs (8) depends on the size of the gas turbine and thus on the outlet cross-section of the gas ring channel (1) and is approximately 10% of the width 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)

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EP1391583A1 EP1391583A1 (en) 2004-02-25
EP1391583B1 true 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)
CA (1) CA2424166C (en)
DE (2) DE10239534A1 (en)

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* Cited by examiner, † Cited by third party
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EP2157286A1 (en) * 2008-08-21 2010-02-24 Siemens Aktiengesellschaft Gas turbine comprising angled duct and method for guiding the flow onto the turbine
EP2157285A1 (en) * 2008-08-21 2010-02-24 Siemens Aktiengesellschaft Gas turbine assembly and method for guiding the flow onto the turbine
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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Also Published As

Publication number Publication date
EP1391583A1 (en) 2004-02-25
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
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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