EP1351022A2 - Air passage for turbine combustor with shingles - Google Patents
Air passage for turbine combustor with shingles Download PDFInfo
- Publication number
- EP1351022A2 EP1351022A2 EP03001782A EP03001782A EP1351022A2 EP 1351022 A2 EP1351022 A2 EP 1351022A2 EP 03001782 A EP03001782 A EP 03001782A EP 03001782 A EP03001782 A EP 03001782A EP 1351022 A2 EP1351022 A2 EP 1351022A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- shingle
- air hole
- mixed air
- gas turbine
- 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
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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
- F23R3/02—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
- F23R3/002—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
- 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 gas turbine combustor with combustion chamber shingles, with the combustion chamber shingles on a support structure of the gas turbine combustion chamber are attached and each have at least one mixed air hole, which arranged in alignment with a mixed air hole in the supporting structure is.
- the constructions known from the prior art are formed so that the diameter of the mixed air hole Support structure (shingle support) at most slightly larger is than the diameter of the mixed air hole of the combustion chamber shingle.
- the difference in size is used in the prior art just to make sure that the worst possible combination of all manufacturing and assembly tolerances the edge of the Mixing air hole of the combustion chamber shingle not from the edge of the Mixed air hole of the support structure is towered over.
- the object of the invention is a gas turbine combustion chamber with combustion chamber shingles of the type mentioned To create kind, which with simple construction, simpler, less expensive Manufacturability and easy assembly a high Has lifespan and overheating of the entire construction avoids.
- the diameter of the Mixed air hole of the support structure is significantly larger than that Diameter of the mixed air hole in the combustion chamber shingle.
- the configuration according to the invention is characterized by a A number of significant advantages.
- Diameter of the mixed air hole of the support structure and the Mixing air hole of the combustion chamber shingle can be achieved that due to the strong back pressure on the thickened edge of the Combustion chamber shingle when there is a gap between the Combustion chamber shingle and the supporting structure, which by a Overheating of the clapboard is caused, additional Cooling air from the mixed air hole into the interior of the shingle flows and thus intensifies the cooling of the combustion chamber shingle.
- Adaptive cooling is thus implemented according to the invention, in which the amount of cooling air automatically depends on the temperature load the combustion chamber shingle is adjusted.
- the effusion holes can be on the back the surface of the combustion chamber shingle or in the edge of the shingle begin, being on the inside of the shingle or the Support structure facing side can enter.
- the effusion holes end on the surface of the combustion chamber shingle or on the inside of the mixed air hole in the combustion chamber shingle.
- the effusion holes can be without or with a peripheral component around the axis of the mixed air hole. Hot gas side the combustion chamber shingle.
- the amount of cooling air in the initial state the gas turbine combustion chamber can be selected that it is just sufficient for normal operation.
- the maximum amount of air thus stands for the reduction of harmful gas to disposal.
- the Combustion chamber shingle is subjected to greater thermal stress automatically increases the cooling, so that a long-lasting and safe operation is possible.
- Fig. 1 shows a schematic side sectional view of a gas turbine combustor known from the prior art.
- a cover 1 of a combustion chamber head is shown.
- Reference number 2 denotes a base plate
- Combustion chamber shingles are identified by reference number 3.
- the combustion chamber shingles 3 have mixed air holes 4 and are attached to a support structure 6.
- With the reference symbol 5 is a heat shield with a hole for a burner Designated 8.
- a turbine guide vane is located at the outlet of the combustion chamber 9 is shown schematically.
- the reference number 10 denotes a guide vane in the compressor outlet.
- On Combustion chamber outer casing 11 and a combustion chamber inner casing 12 limits the combustion chamber.
- Fig. 2a and 2b show the design of a mixed air hole 4 of the combustion chamber shingle 3 and a corresponding one Mixed air hole of the support structure 6 according to the prior art. It can be seen that the diameter 13 of the Mixed air hole of the support structure 6 is slightly larger, than the diameter 14 of the mixed air hole 4 of the combustion chamber shingle 3. From Fig. 2b it can be seen that the air flow 15 in the mixed air hole 4, additional air from the interior of the shingle draws.
- Figures 3a and 3b show the configuration according to the invention in an analogous representation to Figs. 2a and 2b. It can be seen that the diameter 13 of the mixed air hole of the Support structure 6 is clearer or significantly larger than that Diameter 14 of the mixed air hole 4 of the combustion chamber shingle 3. From Fig. 3b it can be seen that a dynamic pressure of the Air flow 15 for an additional inflow of cooling air leads into the interior of the shingle as soon as there is a gap forms between the support structure 6 and the shingle edge 7.
- Fig. 4a shows a partial area in an enlarged view a combustion chamber shingle according to the invention 3 it can be seen that by the shingle edge 7 in the area of the mixed air hole 4 additional effusion holes 16 are provided are to cool air from the shingle interior to feed the combustion chamber shingle 3.
- the effusion holes 16 in different orientations be arranged to the level of the combustion chamber shingle 3.
- the Effusion hole 16a is arranged at a very shallow angle, while the effusion holes 16b and 16d extend through the Shingle edge 7 extend and at a larger angle to Main plane of the combustion chamber shingle 3 are aligned.
- the Effusion hole 16e extends almost perpendicular to the main plane the combustion chamber shingle 3 and flows through the edge of the shingle 7th
- Fig. 4b shows two different versions of the effusion holes 16 in the top view of the mixed air hole 4 of the combustion chamber shingle 3.
- the effusion holes are each arranged radially (regardless of the respective angle of inclination according to Fig. 4a), while in the right figure of Fig. 4b an additional Tangential components around the axis of the mixed air hole or a tangential arrangement of the effusion holes 16 is realized is. This enables particularly efficient cooling respectively.
Abstract
Description
Die Erfindung bezieht sich auf eine Gasturbinenbrennkammer mit Brennkammerschindeln, wobei die Brennkammerschindeln an einer Tragstruktur der Gasturbinenbrennkammer befestigt sind und jeweils zumindest ein Mischluftloch aufweisen, welches fluchtend zu einem Mischluftloch der Tragstruktur angeordnet ist.The invention relates to a gas turbine combustor with combustion chamber shingles, with the combustion chamber shingles on a support structure of the gas turbine combustion chamber are attached and each have at least one mixed air hole, which arranged in alignment with a mixed air hole in the supporting structure is.
Aus dem Stand der Technik ist es bekannt, Schindeln in Gasturbinenbrennkammern einzusetzen, um die Trag- und Dichtstruktur vor der intensiven Wärmeeinstrahlung der Flamme zu schützen. Die Tragstruktur bleibt dadurch relativ kühl und behält ihre mechanische Festigkeit. Demgemäß ist es erforderlich, Mischluft durch ein Mischluftloch in der Tragstruktur sowie durch ein Mischluftloch der Brennkammerschindel von außen von einem Ringkanal nach innen in die Brennkammer zu führen.It is known from the prior art to shingles in gas turbine combustion chambers used to support and seal structure before the intense heat of the flame protect. The support structure remains relatively cool and maintains its mechanical strength. Accordingly, it is necessary Mixed air through a mixed air hole in the supporting structure and through a mixed air hole in the combustion chamber shingle from the outside from an annular channel into the combustion chamber respectively.
Derartige Konstruktionen sind beispielsweise aus der US 6,145,319 oder EP 972 992 A2 bekannt.Such constructions are for example from the US 6,145,319 or EP 972 992 A2.
Die aus dem Stand der Technik bekannten Konstruktionen sind so ausgebildet, dass der Durchmesser des Mischluftloches der Tragstruktur (Schindelträger) höchstens geringfügig größer ist, als der Durchmesser des Mischluftlochs der Brennkammerschindel. Der Größenunterschied dient beim Stand der Technik nur dazu, sicherzustellen, dass bei der ungünstigsten Kombination aller Fertigungs- und Montagetoleranzen der Rand des Mischluftlochs der Brennkammerschindel nicht vom Rand des Mischluftlochs der Tragstruktur überragt wird.The constructions known from the prior art are formed so that the diameter of the mixed air hole Support structure (shingle support) at most slightly larger is than the diameter of the mixed air hole of the combustion chamber shingle. The difference in size is used in the prior art just to make sure that the worst possible combination of all manufacturing and assembly tolerances the edge of the Mixing air hole of the combustion chamber shingle not from the edge of the Mixed air hole of the support structure is towered over.
Falls nun während des Betriebes ein Spalt zwischen dem Schindelrand und der Tragstruktur auftritt, entweicht durch diesen wegen der großen Druckdifferenz zwischen dem Schindelinnenraum und dem Mischluftloch relativ viel Kühlluft.If there is a gap between the Shingle edge and the supporting structure occurs, escapes through this because of the large pressure difference between the interior of the shingle and the mixed air hole relatively much cooling air.
Um zu verhindern, dass durch die dabei auftretende Überhitzung die Brennkammerschindel vorzeitig versagt, muss deutlich mehr Kühlluft durch die Brennkammerschindel geleitet werden. Diese zusätzliche Kühlluft steht somit nicht mehr für eine Verbesserung der Brennstoffaufbereitung und der damit verbundenen Stickoxidemissionsverminderung zur Verfügung.To prevent it from overheating the combustion chamber shingle fails prematurely must be clear more cooling air passed through the combustion chamber shingle become. This additional cooling air is therefore no longer available for an improvement in fuel processing and with it associated nitrogen oxide emission reduction available.
Der Erfindung liegt die Aufgabe zu Grunde, eine Gasturbinenbrennkammer mit Brennkammerschindeln der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau, einfacher, kostengünstiger Herstellbarkeit und einfacher Montage eine hohe Lebensdauer aufweist und Überhitzungen der gesamten Konstruktion vermeidet.The object of the invention is a gas turbine combustion chamber with combustion chamber shingles of the type mentioned To create kind, which with simple construction, simpler, less expensive Manufacturability and easy assembly a high Has lifespan and overheating of the entire construction avoids.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Hauptanspruchs gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention, the object is achieved by the combination of features of the main claim, the sub-claims show further advantageous embodiments of the invention.
Erfindungsgemäß ist vorgesehen, dass der Durchmesser des Mischluftlochs der Tragstruktur deutlich größer ist, als der Durchmesser des Mischluftlochs der Brennkammerschindel.According to the invention it is provided that the diameter of the Mixed air hole of the support structure is significantly larger than that Diameter of the mixed air hole in the combustion chamber shingle.
Die erfindungsgemäße Ausgestaltung zeichnet sich durch eine Reihe erheblicher Vorteile aus.The configuration according to the invention is characterized by a A number of significant advantages.
Durch die erfindungsgemäße Wahl der Durchmesserverhältnisse steht der Schindelrand, von der Außenseite der Tragstruktur aus gesehen, deutlich sichtbar in den freien Durchmesser des Mischluftloches vor. Hierdurch bildet sich ein Staudruck auf dem verdickten Schindelrand. Weiterhin wird der Durchflusskoeffizient des Mischluftloches erhöht. Tritt nun im Betrieb ein Spalt zwischen dem Schindelrand und dem der Tragstruktur auf, dann wirkt der oben genannte Staudruck einem Ausströmen von Kühlluft aus dem Schindelinnenraum entgegen. Bei entsprechender Wahl des Durchmessers des Mischluftloches der Tragstruktur ist der Staudruck auf dem Schindelrand gleich dem Druck im Schindelinnenraum. Somit wird ein Ausströmen von Kühlluft aus dem Schindelinnenraum gänzlich verhindert.Through the choice of diameter ratios according to the invention stands the edge of the shingle from the outside of the supporting structure seen from clearly visible in the free diameter of the Mixed air hole before. This creates a dynamic pressure the thickened edge of the shingle. Furthermore, the flow coefficient of the mixed air hole increased. Now occurs in operation a gap between the edge of the shingle and that of the supporting structure then the above-mentioned dynamic pressure acts on an outflow of cooling air from the interior of the shingle. With appropriate Choice of the diameter of the mixed air hole Supporting structure, the dynamic pressure on the edge of the shingle is the same the pressure inside the shingle. Thus there is an outflow completely prevented by cooling air from the interior of the shingle.
Erfindungsgemäß kann bei einer entsprechenden Abstimmung der Durchmesser des Mischluftlochs der Tragstruktur und des Mischluftlochs der Brennkammerschindel erreicht werden, dass durch den starken Staudruck auf dem verdickten Rand der Brennkammerschindel beim Auftreten eines Spalts zwischen der Brennkammerschindel und der Tragstruktur, welcher durch eine Überhitzung der Schindel hervorgerufen wird, zusätzliche Kühlluft aus dem Mischluftloch in den Schindelinnenraum fließt und damit die Kühlung der Brennkammerschindel intensiviert.According to the invention can with a corresponding vote Diameter of the mixed air hole of the support structure and the Mixing air hole of the combustion chamber shingle can be achieved that due to the strong back pressure on the thickened edge of the Combustion chamber shingle when there is a gap between the Combustion chamber shingle and the supporting structure, which by a Overheating of the clapboard is caused, additional Cooling air from the mixed air hole into the interior of the shingle flows and thus intensifies the cooling of the combustion chamber shingle.
Erfindungsgemäß ist somit eine adaptive Kühlung realisiert, bei welcher die Kühlluftmenge selbsttätig an die Temperaturbelastung der Brennkammerschindel angepasst wird.Adaptive cooling is thus implemented according to the invention, in which the amount of cooling air automatically depends on the temperature load the combustion chamber shingle is adjusted.
Erfindungsgemäß wird der verdickte Rand der Brennkammerschindel durch ein gesondertes Muster von Effusionslöchern gekühlt. Die Effusionslöcher können dabei auf der Rückseite der Oberfläche der Brennkammerschindel oder im Schindelrand beginnen, wobei sie auf der dem Schindelinnenraum oder der Tragstruktur zugewandten Seite eintreten können. Die Effusionslöcher enden auf der Oberfläche der Brennkammerschindel oder an der Innenseite des Mischluftlochs der Brennkammerschindel. Die Effusionslöcher können ohne oder mit einer Umfangskomponente um die Achse des Mischluftloches zur. Heißgasseite der Brennkammerschindel verlaufen.According to the thickened edge of the combustion chamber shingle through a separate pattern of effusion holes cooled. The effusion holes can be on the back the surface of the combustion chamber shingle or in the edge of the shingle begin, being on the inside of the shingle or the Support structure facing side can enter. The effusion holes end on the surface of the combustion chamber shingle or on the inside of the mixed air hole in the combustion chamber shingle. The effusion holes can be without or with a peripheral component around the axis of the mixed air hole. Hot gas side the combustion chamber shingle.
Es ergibt sich somit, dass die Kühlluftmenge im Ausgangszustand der Gasturbinenbrennkammer so gewählt werden kann, dass sie für den normalen Betrieb gerade ausreichend ist. Somit steht die maximale Luftmenge für die Schadgasreduzierung zur Verfügung. In Extremsituationen, bei denen die Brennkammerschindel thermisch stärker belastet wird, wird selbsttätig die Kühlung erhöht, sodass ein langanhaltender und sicherer Betrieb möglich ist.It follows that the amount of cooling air in the initial state the gas turbine combustion chamber can be selected that it is just sufficient for normal operation. The maximum amount of air thus stands for the reduction of harmful gas to disposal. In extreme situations where the Combustion chamber shingle is subjected to greater thermal stress automatically increases the cooling, so that a long-lasting and safe operation is possible.
Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:
- Abb. 1
- eine schematische Schnittansicht einer Gasturbinenbrennkammer mit Brennkammerschindeln gemäß dem Stand der Technik,
- Abb. 2a
- eine Schnittansicht durch eine Brennkammerschindel nach dem Stand der Technik,
- Abb. 2b
- eine Detailansicht des
Details 2b von Abb. 2a, - Abb. 3a
- eine Schnittansicht, analog Abb. 2a einer erfindungsgemäßen Ausgestaltung einer Brennkammerschindel,
- Abb. 3b
- eine Detailansicht des
Details 3b von Abb. 3a, - Abb. 4a
- eine Detaildarstellung des Brennkammerschindelrandes analog zu der Darstellung der Abb. 3a, und
- Abb. 4b
- Darstellungen des Randbereichs eines erfindungsgemäßen Mischluftloches in Draufsicht mit unterschiedlicher Anordnung von Effusionslöchern.
- Fig. 1
- 1 shows a schematic sectional view of a gas turbine combustion chamber with combustion chamber shingles according to the prior art,
- Fig.2a
- 2 shows a sectional view through a combustion chamber shingle according to the prior art,
- Fig.2b
- a detailed view of
detail 2b of Fig. 2a, - Fig.3a
- 2 shows a sectional view, analogous to FIG. 2a, of an embodiment of a combustion chamber shingle according to the invention,
- Fig.3b
- a detailed view of
detail 3b of Fig. 3a, - Fig.4a
- a detailed representation of the combustion chamber shingle edge analogous to the representation of Fig. 3a, and
- Fig.4b
- Top view representations of the edge region of a mixed air hole according to the invention with different arrangement of effusion holes.
Die Abb. 1 zeigt eine schematische Seiten-Schnittansicht einer
aus dem Stand der Technik bekannten Gasturbinenbrennkammer.
Dabei ist eine Abdeckung 1 eines Brennkammerkopfes dargestellt.
Das Bezugszeichen 2 bezeichnet eine Grundplatte,
Brennkammerschindeln sind mit dem Bezugszeichen 3 bezeichnet.
Die Brennkammerschindeln 3 weisen Mischluftlöcher 4 auf
und sind an einer Tragstruktur 6 befestigt. Mit dem Bezugszeichen
5 ist ein Hitzeschild mit einem Loch für einen Brenner
8 bezeichnet. Am Auslauf der Brennkammer ist eine Turbinenleitschaufel
9 schematisch dargestellt. Das Bezugszeichen
10 bezeichnet eine Leitschaufel im Verdichterauslass. Ein
Brennkammeraußengehäuse 11 und ein Brennkammerinnengehäuse
12 begrenzt die Brennkammer.Fig. 1 shows a schematic side sectional view of a
gas turbine combustor known from the prior art.
A
Die Abb. 2a und 2b zeigen die Ausgestaltung eines Mischluftlochs
4 der Brennkammerschindel 3 sowie eines entsprechenden
Mischluftloches der Tragstruktur 6 gemäß dem Stand der Technik.
Dabei ist ersichtlich, dass der Durchmesser 13 des
Mischluftlochs der Tragstruktur 6 geringfügig größer ist,
als der Durchmesser 14 des Mischluftlochs 4 der Brennkammerschindel
3. Aus Abb. 2b ist ersichtlich, dass die Luftströmung
15 im Mischluftloch 4 zusätzlich Luft aus dem Schindelinnenraum
zieht.Fig. 2a and 2b show the design of a
Die Abb. 3a und 3b zeigen die erfindungsgemäße Ausgestaltung
in analoger Darstellung zu den Abb. 2a und 2b. Dabei ist ersichtlich,
dass der Durchmesser 13 des Mischluftlochs der
Tragstruktur 6 deutlicher oder erheblich größer ist, als der
Durchmesser 14 des Mischluftlochs 4 der Brennkammerschindel
3. Aus der Abb. 3b ist ersichtlich, dass ein Staudruck der
Luftströmung 15 zu einem zusätzlichen Einströmen von Kühlluft
in den Schindelinnenraum führt, sobald sich ein Spalt
zwischen der Tragstruktur 6 und dem Schindelrand 7 bildet.Figures 3a and 3b show the configuration according to the invention
in an analogous representation to Figs. 2a and 2b. It can be seen
that the
Die Abb. 4a zeigt in vergrößerter Darstellung einen Teilbereich
einer erfindungsgemäßen Brennkammerschindel 3. Dabei
ist ersichtlich, dass durch den Schindelrand 7 im Bereich
des Mischluftlochs 4 zusätzliche Effusionslöcher 16 vorgesehen
sind, um Kühlluft aus dem Schindelinnenraum zur Kühlung
der Brennkammerschindel 3 zuzuführen. Wie ersichtlich, können
die Effusionslöcher 16 in unterschiedlicher Ausrichtung
zu der Ebene der Brennkammerschindel 3 angeordnet sein. Das
Effusionsloch 16a ist mit einem sehr flachen Winkel angeordnet,
während die Effusionslöcher 16b und 16d sich durch den
Schindelrand 7 erstrecken und in einem größeren Winkel zur
Hauptebene der Brennkammerschindel 3 ausgerichtet sind. Das
Effusionsloch 16e erstreckt nahezu senkrecht zur Hauptebene
der Brennkammerschindel 3 und durchströmt den Schindelrand
7.Fig. 4a shows a partial area in an enlarged view
a combustion chamber shingle according to the
Die Abb. 4b zeigt zwei unterschiedliche Ausführungsvarianten
der Effusionslöcher 16 in der Draufsicht auf das Mischluftloch
4 der Brennkammerschindel 3. In der linken Figur der
Abb. 4b sind die Effusionslöcher jeweils radial angeordnet
(unabhängig von dem jeweiligen Neigungswinkel gemäß Abb.
4a), während in der rechten Figur der Abb. 4b zusätzlich eine
Tangentialkomponenten um die Achse des Mischluftloches
oder eine tangentiale Anordnung der Effusionslöcher 16 realisiert
ist. Hierdurch kann eine besonders effiziente Kühlung
erfolgen.Fig. 4b shows two different versions
of the effusion holes 16 in the top view of the
Die Erfindung ist nicht auf die gezeigten Ausführungsbeispiele beschränkt, vielmehr ergeben sich im Rahmen der Er-findung vielfältige Abwandlungs- und Modifikationsmöglichkeiten.The invention is not based on the exemplary embodiments shown limited, rather arise within the scope of the invention diverse options for modification and modification.
- 11
- Abdeckung des BrennkammerkopfesCover of the combustion chamber head
- 22
- Grundplattebaseplate
- 33
- Brennkammerschindelcombustion chamber tile
- 44
- MischluftlochMixed air hole
- 55
- Hitzeschild (mit Loch für Brenner)Heat shield (with hole for burner)
- 66
- Tragstruktursupporting structure
- 77
- Schindelrandtile rim
- 88th
- Brenner (mit Brennerarm und Drallerzeuger)Burner (with burner arm and swirl generator)
- 99
- Turbinenleitschaufelturbine vane
- 1010
- Leitschaufel im VerdichterauslassGuide vane in the compressor outlet
- 1111
- BrennkammeraußengehäuseCombustion chamber outer housing
- 1212
- BrennkammerinnengehäuseCombustion chamber inner housing
- 1313
-
Durchmesser des Mischluftlochs in der Tragstruktur 6Diameter of the mixed air hole in the
support structure 6 - 1414
-
Durchmesser des Mischluftlochs 4 in der Schindel 3Diameter of the
mixed air hole 4 in theshingle 3 - 1515
-
Luftströmung im Mischluftloch 4Air flow in the
mixed air hole 4 - 1616
- Effusionslocheffusion
Claims (10)
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10214570A DE10214570A1 (en) | 2002-04-02 | 2002-04-02 | Mixed air hole in gas turbine combustion chamber with combustion chamber shingles |
| DE10214570 | 2002-04-02 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1351022A2 true EP1351022A2 (en) | 2003-10-08 |
| EP1351022A3 EP1351022A3 (en) | 2005-01-26 |
| EP1351022B1 EP1351022B1 (en) | 2010-08-04 |
Family
ID=27816106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03001782A Expired - Fee Related EP1351022B1 (en) | 2002-04-02 | 2003-01-28 | Air passage for turbine combustor with shingles |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US7059133B2 (en) |
| EP (1) | EP1351022B1 (en) |
| DE (2) | DE10214570A1 (en) |
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| EP2172708A3 (en) * | 2008-10-01 | 2014-05-14 | United Technologies Corporation | Structures with adaptive cooling |
| EP2738470A1 (en) * | 2012-11-28 | 2014-06-04 | Rolls-Royce Deutschland Ltd & Co KG | Shingle attachment assembly of a gas turbine combustion chamber |
| EP2971668A4 (en) * | 2013-03-12 | 2016-03-02 | United Technologies Corp | Active cooling of grommet bosses for a combustor panel of a gas turbine engine |
| EP3077727A4 (en) * | 2013-12-06 | 2016-12-07 | United Technologies Corp | Cooling a quench aperture body of a combustor wall |
| EP3306196A1 (en) * | 2016-10-06 | 2018-04-11 | Rolls-Royce Deutschland Ltd & Co KG | Combustion chamber assembly of a gas turbine and aviation gas turbine |
| EP3431875A1 (en) * | 2017-07-19 | 2019-01-23 | United Technologies Corporation | Dilution holes for gas turbine engines |
| US11137140B2 (en) | 2017-10-04 | 2021-10-05 | Raytheon Technologies Corporation | Dilution holes with ridge feature for gas turbine engines |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7104065B2 (en) * | 2001-09-07 | 2006-09-12 | Alstom Technology Ltd. | Damping arrangement for reducing combustion-chamber pulsation in a gas turbine system |
| EP1507116A1 (en) * | 2003-08-13 | 2005-02-16 | Siemens Aktiengesellschaft | Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber |
| US7140185B2 (en) * | 2004-07-12 | 2006-11-28 | United Technologies Corporation | Heatshielded article |
| US8161752B2 (en) * | 2008-11-20 | 2012-04-24 | Honeywell International Inc. | Combustors with inserts between dual wall liners |
| US9010121B2 (en) | 2010-12-10 | 2015-04-21 | Rolls-Royce Plc | Combustion chamber |
| US9062884B2 (en) | 2011-05-26 | 2015-06-23 | Honeywell International Inc. | Combustors with quench inserts |
| GB201116608D0 (en) * | 2011-09-27 | 2011-11-09 | Rolls Royce Plc | A method of operating a combustion chamber |
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- 2003-01-28 DE DE50312938T patent/DE50312938D1/en not_active Expired - Lifetime
- 2003-03-28 US US10/400,553 patent/US7059133B2/en not_active Expired - Fee Related
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| EP2172708A3 (en) * | 2008-10-01 | 2014-05-14 | United Technologies Corporation | Structures with adaptive cooling |
| US9587832B2 (en) | 2008-10-01 | 2017-03-07 | United Technologies Corporation | Structures with adaptive cooling |
| EP2738470A1 (en) * | 2012-11-28 | 2014-06-04 | Rolls-Royce Deutschland Ltd & Co KG | Shingle attachment assembly of a gas turbine combustion chamber |
| US9341372B2 (en) | 2012-11-28 | 2016-05-17 | Rolls-Royce Deutschland Ltd & Co Kg | Tile fastening arrangement of a gas-turbine combustion chamber |
| EP2971668A4 (en) * | 2013-03-12 | 2016-03-02 | United Technologies Corp | Active cooling of grommet bosses for a combustor panel of a gas turbine engine |
| EP3077727A4 (en) * | 2013-12-06 | 2016-12-07 | United Technologies Corp | Cooling a quench aperture body of a combustor wall |
| EP3306196A1 (en) * | 2016-10-06 | 2018-04-11 | Rolls-Royce Deutschland Ltd & Co KG | Combustion chamber assembly of a gas turbine and aviation gas turbine |
| US10712006B2 (en) | 2016-10-06 | 2020-07-14 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber arrangement of a gas turbine and aircraft gas turbine |
| EP3431875A1 (en) * | 2017-07-19 | 2019-01-23 | United Technologies Corporation | Dilution holes for gas turbine engines |
| US10408453B2 (en) | 2017-07-19 | 2019-09-10 | United Technologies Corporation | Dilution holes for gas turbine engines |
| US11137140B2 (en) | 2017-10-04 | 2021-10-05 | Raytheon Technologies Corporation | Dilution holes with ridge feature for gas turbine engines |
Also Published As
| Publication number | Publication date |
|---|---|
| US20030182942A1 (en) | 2003-10-02 |
| DE10214570A1 (en) | 2004-01-15 |
| US7059133B2 (en) | 2006-06-13 |
| EP1351022A3 (en) | 2005-01-26 |
| DE50312938D1 (en) | 2010-09-16 |
| EP1351022B1 (en) | 2010-08-04 |
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