WO2005019730A1 - Hitzeschildanordnung für eine ein heissgas führende komponente, insbesondere für eine brennkammer einer gasturbine - Google Patents
Hitzeschildanordnung für eine ein heissgas führende komponente, insbesondere für eine brennkammer einer gasturbine Download PDFInfo
- Publication number
- WO2005019730A1 WO2005019730A1 PCT/EP2004/008116 EP2004008116W WO2005019730A1 WO 2005019730 A1 WO2005019730 A1 WO 2005019730A1 EP 2004008116 W EP2004008116 W EP 2004008116W WO 2005019730 A1 WO2005019730 A1 WO 2005019730A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- heat shield
- coolant
- hot gas
- combustion chamber
- cooling
- Prior art date
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
- F23R3/002—Wall structures
-
- 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
- F23M5/00—Casings; Linings; Walls
- F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
-
- 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
- F23M5/00—Casings; Linings; Walls
- F23M5/08—Cooling thereof; Tube walls
- F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
-
- 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
- F23R2900/00012—Details of sealing devices
Definitions
- Heat shield arrangement for a component carrying a hot gas, in particular for a combustion chamber of a gas turbine
- the invention relates to a heat shield arrangement for a component carrying a hot gas, which comprises a plurality of heat shield elements which are arranged next to one another on a support structure while leaving a gap, wherein a heat shield element can be attached to the support structure, so that an interior is formed which is partially covered by a to be cooled hot gas wall is limited, with an inlet channel for the inflow of a coolant in the interior.
- the invention further relates to a combustion chamber with an inner combustion chamber lining, which has such a heat shield arrangement, and to a gas turbine with such a combustion chamber.
- EP 0 224 817 B1 describes a heat shield arrangement, in particular for structural parts of gas turbine systems.
- the heat shield arrangement serves to protect a support structure against a hot fluid, in particular for Protection of a hot gas duct wall in gas turbine plants.
- the heat shield arrangement has an inner lining made of heat-resistant material, which is composed of heat shield elements anchored to the support structure to cover the entire surface. These heat shield elements are arranged next to one another while leaving gaps for the flow of cooling fluid and can be moved by heat.
- Each of these heat shield elements has a hat part and a shaft part in the manner of a mushroom.
- the hat part is a flat or spatial, polygonal plate body with straight or curved edge lines.
- the shaft part connects the central area of the plate body with the support structure.
- the hat part preferably has a triangular shape, which means that identical hat parts can be used to produce an inner lining of almost any geometry.
- the hat parts and possibly other parts of the heat shield elements consist of a high-temperature-resistant material, in particular of a steel.
- the support structure has bores through which a cooling fluid, in particular air, can flow into an intermediate space between the hat part and the support structure and from there through the gaps to flow through the
- Cooling fluid can flow into a space area surrounded by the heat shield elements, for example a combustion chamber of a gas turbine system. This flow of cooling fluid reduces the penetration of hot gas into the space.
- US-5,216,886 describes a metallic liner for a combustion chamber.
- This lining consists of a large number of cube-shaped hollow components (cells) arranged side by side, which are welded or soldered to a common metal plate.
- the common metal plate has in each case assigned to each cube-shaped cell exactly one opening for the inflow of cooling fluid.
- the cubic cells are arranged next to each other, leaving a gap. They contain a respective opening for the outflow of cooling fluid on each side wall in the vicinity of the common metal plate.
- the cooling fluid therefore enters the gaps between adjacent cube-shaped cells and flows through this column and forms a cooling film on a surface of the cells which can be exposed to hot gas and which is directed parallel to the metallic plate.
- an open cooling system is defined in which cooling air enters the interior of the combustion chamber through a wall structure through the cells. The cooling air is therefore lost for further cooling purposes.
- the wall in particular for gas turbine plants, which has cooling fluid channels.
- the wall is preferably arranged between a hot space and a cooling fluid space. It is assembled from individual wall elements, each of the wall elements being a plate body made of high-temperature resistant material. Each plate body has cooling channels which are distributed over one another and parallel to one another and which communicate with a cooling fluid space at one end and with the hot space at the other end. The cooling fluid flowing into the hot space and guided through the cooling fluid channels forms a cooling fluid film on the surface of the wall element and / or adjacent wall elements facing the hot space.
- GB-A-849255 shows a cooling system for cooling a combustion chamber wall.
- the combustion chamber wall is formed by wall elements.
- Each wall element has a hot gas wall with an outside that can be subjected to hot gas and with an inside.
- Nozzles are arranged perpendicular to the inside. Cooling fluid emerges from these nozzles in the form of a concentrated stream and hits the inside. This cools the hot gas wall.
- the cooling fluid is collected in a collection chamber and removed from the collection chamber.
- the object of the invention is to provide a heat shield arrangement which can be cooled with a coolant, so that when the heat shield arrangement is cooled, there is at most a slight loss of cooling fluid.
- the heat shield arrangement should be usable in a combustion chamber of a gas turbine.
- a heat shield arrangement for a component carrying a hot gas which comprises a plurality of heat shield elements arranged next to one another on a support structure while leaving a gap, a heat shield element being attachable to the support structure, so that an interior space is formed , which is delimited in some areas by a hot gas wall to be cooled, with an inlet channel for the inflow of a coolant into the interior, for the controlled exit of coolants. tel from the interior, a coolant outlet channel is provided, which opens into the gap from the interior.
- the invention is based on the consideration that due to the very high flame temperatures in hot gas channels or other hot gas spaces, for example in combustion chambers of stationary gas turbines, the components carrying hot gas have to be actively cooled.
- the most frequently used cooling concepts are convection cooling, convection cooling with measures to increase turbulence, and impingement cooling. Due to the very intensive efforts in particular to reduce the pollutant emissions from open-cooled systems, for example from open-cooled combustion chambers of gas turbines, the saving of cooling air is a particularly important factor in achieving these goals - here an increased NO x reduction.
- the goal for openly cooled cooling concepts is therefore to minimize the required cooling air mass flow.
- the cooling air ultimately escapes through the gap between adjacent heat shield elements after the cooling task has been carried out, in order to subsequently reach the combustion chamber.
- the outflow of the cooling air protects the system against the penetration of hot gas into the gaps. Due to the uncontrolled blowing out of the cooling air, more cooling air is used to block the gaps than is necessary for the cooling fans. This overdosing leads to excessive cooling air consumption, with disadvantageous consequences for the overall system efficiency and the pollutant emissions of the combustion system that generates the hot gas.
- the heat shield arrangement of the invention now for the first time proposes a controlled and targeted outlet of the coolant after performing the cooling task on the hot gas wall to be cooled for an open cooling system.
- the heat shield arrangement is particularly easy to implement and, compared to the closed cooling concepts with coolant return, structurally connected with considerably less manufacturing effort.
- the controlled coolant outlet into the gap can coolant, z. B. cooling air, can be saved and at the same time a significant reduction in pollutant emissions are effected, in particular the NO x emission. This is achieved in that a coolant outlet channel is provided for the controlled exit of coolant from the interior which opens into the gap from the interior.
- a particularly high cooling efficiency and blocking effect of the coolant against hot gas attack in the gap on the support structure is hereby achieved in the gap through the targeted and metered application of coolant.
- the controlled exit of coolant from the interior can be carried out in a simple manner by appropriate dimensioning of the coolant outlet channel, for example with regard to the channel cross section and the channel length.
- the heat shield element has a side wall which is inclined in relation to the hot gas wall in the direction of the support structure.
- the heat shield element is designed in its basic geometry as a single-shell hollow body which can be attached to the support structure, the interior being formed. The interior is bounded or fixed in exactly one direction by the support structure and in the other spatial directions by the heat shield element itself.
- the coolant outlet channel penetrates the side wall.
- the coolant outlet channel can be designed simply as a bore through the side wall, the interior being connected to the gap space formed by the gap. This means that coolant can due to the pressure difference between the interior and the gap defined by the gap emerge in a controlled manner from the interior through the coolant outlet channel.
- a sealing element is preferably attached between the side wall and the support structure. Due to the inclination of the side wall in the direction of the support structure, when the heat shield element is detachably attached to the support structure, a gap can be provided for thermomechanical reasons, which gap can lead to undesirable coolant leaks. It is therefore particularly advantageous to seal any gaps that can lead to an uncontrolled blowing out of coolant from the interior by means of suitable sealing measures. This provides a tight connection between the heat shield element and the support structure.
- the sealing element between the side wall and the support structure is a particularly simple but effective measure to further reduce the coolant consumption.
- the sealing element can additionally assume a damping function, so that the heat shield elements of the heat shield arrangement are mechanically dampened on the support structure.
- Impingement cooling is a particularly effective method of cooling the heat shield arrangement, the coolant hitting the hot gas wall in a plurality of discrete coolant jets perpendicular to the hot gas wall and cooling the hot gas wall efficiently from the interior accordingly.
- the impact cooling device is preferably formed by a multiplicity of inlet channels for coolants which are introduced into the support structure. Through a corresponding plurality of inlet channels, which are in an interior of a Impact cooling device is already realized in a simple manner.
- the support structure also has a coolant distribution function due to the large number of inlet channels for the coolant which are introduced into the support structure.
- the inlet channels can be designed as bores in the wall of the support structure.
- the heat shield element consists of a metal or a metal alloy. Highly heat-resistant metallic alloys based on iron, chromium, nickel or cobalt are particularly suitable for this purpose. Since metals or metal alloys are well suited for a casting process, the heat shield element is advantageously designed as a casting.
- the heat shield arrangement is suitable for use in a combustion chamber lining of a combustion chamber.
- a combustion chamber provided with a heat shield arrangement is preferably suitable as a combustion chamber of a gas turbine, in particular a stationary gas turbine.
- FIG. 1 shows a half section through a gas turbine
- FIG. 2 shows a sectional view of a heat shield arrangement according to the invention
- 3 shows a detail view of detail III of the heat shield arrangement shown in FIG. 2
- FIG. 4 shows an alternative embodiment of the heat shield arrangement shown in Figure 3.
- the gas turbine 1 has a compressor 2 for the combustion air, a combustion chamber 4 and a turbine 6 for driving a compressor 2 and a generator, not shown, or a work machine.
- the turbine 6 and the compressor 2 are arranged on a common turbine shaft 8, also referred to as a turbine rotor, to which the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
- the combustion chamber 4, which is designed as an annular combustion chamber, is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
- the turbine 6 has a number of rotatable rotor blades 12 connected to the turbine shaft 8.
- the rotor blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of rows of rotor blades.
- the turbine 6 comprises a number of stationary guide vanes 14, which are also attached to an inner casing 16 of the turbine 6 in a ring shape, with the formation of rows of guide vanes.
- the rotor blades 12 serve to drive the turbine shaft by transmitting impulses from the hot medium, the working medium or the hot gas M flowing through the turbine 6.
- a successive pair from a ring of guide vanes 14 or a guide vane 3 and from a ring of blades 12 or a row of blades is also referred to as a turbine stage.
- Each guide vane 14 has a platform 18, also referred to as a blade root, which is arranged as a wall element for fixing the respective guide vane 14 to the inner housing 16 of the turbine 6.
- the platform 18 is a thermally comparatively heavily loaded component, which forms the outer boundary of a hot gas duct for the working medium M flowing through the turbine 6.
- Each rotor blade 12 is fastened in an analogous manner to the turbine shaft 8 via a platform 20 which is also referred to as a blade root.
- each guide ring 21 is arranged on the inner casing 16 of the turbine 6.
- the outer surface of each guide ring 21 is likewise exposed to the hot working medium M flowing through the turbine 6 and is spaced in the radial direction from the outer end 22 of the rotor blade 12 lying opposite it by a gap.
- the guide rings 21 arranged between adjacent rows of guide vanes serve in particular as cover elements, which protect the inner wall 16 or other housing built-in parts against thermal overloading by the hot working medium M, the hot gas, flowing through the turbine 6.
- the combustion chamber 4 is delimited by a combustion chamber housing 29, a combustion chamber wall 24 being formed on the combustion chamber side.
- the combustion chamber 4 is designed as a so-called annular combustion chamber, in the plurality of which burners 10 arranged in the circumferential direction around the turbine shaft 8 open into a common combustion chamber space.
- the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8.
- the combustion chamber is designed for a comparatively high temperature of the working medium M of approximately 1200 ° C. to 1500 ° C.
- the combustion chamber wall 24 is provided on its side facing the working medium M with a heat shield arrangement 26 which forms a combustion chamber lining. Due to the high temperatures inside the combustion chamber 4, a cooling system is also provided for the heat shield arrangement 26.
- the cooling system is based on the principle of impingement cooling, in which cooling air as coolant K is blown under pressure at a sufficient number of points onto the cooling component perpendicular to its component surface under pressure.
- the cooling system can also be based on the principle of convective cooling or, in addition to impact cooling, this cooling principle can also be used.
- the cooling system is designed for a reliable, area-wide application of coolant K to the heat shield arrangement and, in addition, for particularly low coolant consumption.
- FIG. 2 shows a heat shield arrangement 26 as is particularly suitable for use as a heat-resistant lining of a combustion chamber 4 of a gas turbine 1.
- the heat shield arrangement 26 comprises heat shield elements 26A, 26B, which are arranged next to one another on a support structure 31 while leaving a gap 45.
- the heat shield elements 26A, 26B have a hot gas wall 39 to be cooled, which has a hot side 35 facing the hot gas M and acted upon by the hot gas M during operation, and a cold side 33 opposite the hot side 35.
- the heat shield elements 26A, 26B are cooled from their cold side 33 by a coolant K, for example cooling air, cooled, which is delivered to the interior space 37 formed between the heat shield elements 26A, 26B and the support structure 31 through suitable inlet channels 41, 41A, 41B, 41C and is directed in a direction perpendicular to the cold side 33 of a respective heat shield element 26A, 26B.
- a coolant K for example cooling air
- the at least partially heated air is mixed with the hot gas M.
- a coolant outlet channel 43 is provided, which opens into the gap 45 from the interior 37.
- the plurality of inlet channels 41, 41A, 41B, 41C which are each assigned to an interior 37 of a respective heat shield element 26A, 26B, form an impact cooling device 53, so that the hot gas wall 39 can be cooled particularly effectively by means of impact cooling.
- the inlet channels 41, 41A, 41B, 41C for the coolant K are in this case introduced through corresponding bores in the wall 47 of the support structure.
- the inlet channels 41, 41A, 41B, 41C open into the interior 37 in such a way that the hot gas wall 39 is acted upon vertically.
- the coolant K flows from the interior 37 in a controlled manner through the appropriately dimensioned coolant outlet channel 43 into the gap 45, where a blocking effect against the hot gas M is achieved, which protects the critical components, such as the support structure 31 ,
- FIG 3 shows an enlarged view of detail III of the heat shield arrangement shown in Figure 2.
- the heat shield element 26A has a side wall 49 which is inclined in relation to the hot gas wall 39 in the direction of the support structure 31.
- the heat shield element 26B arranged adjacent to the heat shield element 26A is configured in the same way with a side wall 49.
- the coolant outlet channel 43 is a bore through the side wall 43 of the heat shield elements 26A which opens the side wall 43 into the gap 45 at an oblique angle which rises slightly in the direction of the hot side 35.
- the coolant K leaves the gap 45 after a blocking action has been performed in the gap 45, forming a cooling film of coolant K along the hot side 35 of the heat shield element 26B adjacent to the heat shield element 26A.
- This additional film cooling effect which is achieved with the targeted supply of the coolant K into the gap 45, advantageously provides multiple use of the coolant K for different cooling purposes in the heat shield arrangement 26.
- the side walls 49 do not lie directly on the support structure 31, but are connected to the support structure 31 via a respective sealing element 51.
- the sealing elements 51 perform both a sealing function for the coolant K and a mechanical damping function for the heat shield arrangement 26.
- the sealing element 51 prevents coolant K from coming out of the interior 37 into the gap 45 in an uncontrolled manner and being blown out toward the hot side 35 can be. Rather, the sealing element 51 brings about an additional reduction in the need for coolant K for cooling the heat shield arrangement 26.
- the combination of the sealing element 51 with the coolant outlet duct 43 results in a particularly favorable coolant balance.
- a longitudinal underflow along the wall 47 of the support structure 31 facing the interior 37 is achieved by the sealing elements 51 assigned to the interior 37.
- the tight connection between the heat shield element 26A, 26B and the support structure 31 via the sealing elements 51 is a particularly simple and effective measure to further reduce the coolant consumption.
- telauslasskanal 43 extends through the wall 47 of the support structure 31.
- a targeted delivery of the coolant K into the gap 45 is possible after performing the cooling tasks on a heat shield element 26A.
- the gap 45 and the sealing elements 51 delimiting the gap 45 in the vicinity of the mouth of the coolant outlet channel 43 are thereby cooled.
- the side walls 49 delimiting the gap 45 are additionally cooled convectively.
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
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2006522925A JP4436837B2 (ja) | 2003-08-13 | 2004-07-20 | 燃焼ガスを案内する構成要素 |
EP04763361.5A EP1654495B1 (de) | 2003-08-13 | 2004-07-20 | Hitzeschildanordnung für eine ein heissgas führende komponente, insbesondere für eine brennkammer einer gasturbine |
US10/568,115 US7849694B2 (en) | 2003-08-13 | 2004-07-20 | Heat shield arrangement for a component guiding a hot gas in particular for a combustion chamber in a gas turbine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03018415.4 | 2003-08-13 | ||
EP03018415A EP1507116A1 (de) | 2003-08-13 | 2003-08-13 | Hitzeschildanordnung für eine ein Heissgas führende Komponente, insbesondere für eine Brennkammer einer Gasturbine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005019730A1 true WO2005019730A1 (de) | 2005-03-03 |
Family
ID=33560795
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2004/008116 WO2005019730A1 (de) | 2003-08-13 | 2004-07-20 | Hitzeschildanordnung für eine ein heissgas führende komponente, insbesondere für eine brennkammer einer gasturbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US7849694B2 (de) |
EP (2) | EP1507116A1 (de) |
JP (1) | JP4436837B2 (de) |
CN (1) | CN1829879A (de) |
WO (1) | WO2005019730A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100077764A1 (en) * | 2008-10-01 | 2010-04-01 | United Technologies Corporation | Structures with adaptive cooling |
DE102015205975A1 (de) * | 2015-04-02 | 2016-10-06 | Siemens Aktiengesellschaft | Umführungs-Hitzeschildelement |
Families Citing this family (45)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1650503A1 (de) * | 2004-10-25 | 2006-04-26 | Siemens Aktiengesellschaft | Verfahren zur Kühlung eines Hitzeschildelements und Hitzeschildelement |
DE102005046731A1 (de) * | 2005-04-19 | 2006-11-02 | Siemens Ag | Hitzeschildanordnung |
EP2049840B1 (de) | 2006-08-07 | 2018-04-11 | Ansaldo Energia IP UK Limited | Brennkammer einer verbrennungsanlage |
WO2008017551A2 (de) * | 2006-08-07 | 2008-02-14 | Alstom Technology Ltd | Brennkammer einer verbrennungsanlage |
US8522557B2 (en) | 2006-12-21 | 2013-09-03 | Siemens Aktiengesellschaft | Cooling channel for cooling a hot gas guiding component |
DE102008028025B4 (de) * | 2008-06-12 | 2011-05-05 | Siemens Aktiengesellschaft | Hitzeschildanordnung |
US9534783B2 (en) * | 2011-07-21 | 2017-01-03 | United Technologies Corporation | Insert adjacent to a heat shield element for a gas turbine engine combustor |
EP2549063A1 (de) | 2011-07-21 | 2013-01-23 | Siemens Aktiengesellschaft | Hitzeschildelement für eine Gasturbine |
DE102012204103A1 (de) * | 2012-03-15 | 2013-09-19 | Siemens Aktiengesellschaft | Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer |
EP2728255A1 (de) * | 2012-10-31 | 2014-05-07 | Alstom Technology Ltd | Heißgas-Segmentanordnung |
US9714611B2 (en) | 2013-02-15 | 2017-07-25 | Siemens Energy, Inc. | Heat shield manifold system for a midframe case of a gas turbine engine |
WO2014169127A1 (en) | 2013-04-12 | 2014-10-16 | United Technologies Corporation | Combustor panel t-junction cooling |
US10816201B2 (en) * | 2013-09-13 | 2020-10-27 | Raytheon Technologies Corporation | Sealed combustor liner panel for a gas turbine engine |
EP3047127B1 (de) | 2013-09-16 | 2021-06-23 | Raytheon Technologies Corporation | Angewinkelte kühlungslöcher durch eine transversale struktur einer brennkammerwand einer gasturbinenbrennkammer |
WO2015039074A1 (en) | 2013-09-16 | 2015-03-19 | United Technologies Corporation | Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine |
EP3060847B1 (de) | 2013-10-24 | 2019-09-18 | United Technologies Corporation | Durchgangsgeometrie für eine gasturbinenbrennkammer |
EP3071816B1 (de) * | 2013-11-21 | 2019-09-18 | United Technologies Corporation | Kühlung einer mehrwandigen struktur eines turbinenmotors |
EP3074618B1 (de) * | 2013-11-25 | 2021-12-29 | Raytheon Technologies Corporation | Anordnung für ein turbinentriebwerk |
EP3099976B1 (de) * | 2014-01-30 | 2019-03-13 | United Technologies Corporation | Kühlfluss für führungspaneel in einer gasturbinenbrennkammer |
EP2927592A1 (de) * | 2014-03-31 | 2015-10-07 | Siemens Aktiengesellschaft | Hitzeschildelement, Hitzeschild und Turbinenmaschine |
US10041675B2 (en) | 2014-06-04 | 2018-08-07 | Pratt & Whitney Canada Corp. | Multiple ventilated rails for sealing of combustor heat shields |
JP6282184B2 (ja) | 2014-06-19 | 2018-02-21 | 三菱日立パワーシステムズ株式会社 | 伝熱装置及びそれを備えたガスタービン燃焼器 |
US10012385B2 (en) * | 2014-08-08 | 2018-07-03 | Pratt & Whitney Canada Corp. | Combustor heat shield sealing |
US9534785B2 (en) | 2014-08-26 | 2017-01-03 | Pratt & Whitney Canada Corp. | Heat shield labyrinth seal |
DE102014221225A1 (de) * | 2014-10-20 | 2016-04-21 | Siemens Aktiengesellschaft | Hitzeschildelement und Verfahren zu seiner Herstellung |
US9896970B2 (en) | 2014-11-14 | 2018-02-20 | General Electric Company | Method and system for sealing an annulus |
DE102015202570A1 (de) | 2015-02-12 | 2016-08-18 | Rolls-Royce Deutschland Ltd & Co Kg | Abdichtung eines Randspalts zwischen Effusionsschindeln einer Gasturbinenbrennkammer |
GB201603166D0 (en) * | 2016-02-24 | 2016-04-06 | Rolls Royce Plc | A combustion chamber |
US10619854B2 (en) | 2016-11-30 | 2020-04-14 | United Technologies Corporation | Systems and methods for combustor panel |
US10739001B2 (en) | 2017-02-14 | 2020-08-11 | Raytheon Technologies Corporation | Combustor liner panel shell interface for a gas turbine engine combustor |
US10677462B2 (en) | 2017-02-23 | 2020-06-09 | Raytheon Technologies Corporation | Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor |
US10718521B2 (en) | 2017-02-23 | 2020-07-21 | Raytheon Technologies Corporation | Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor |
US10823411B2 (en) | 2017-02-23 | 2020-11-03 | Raytheon Technologies Corporation | Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor |
US10830434B2 (en) | 2017-02-23 | 2020-11-10 | Raytheon Technologies Corporation | Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor |
US10941937B2 (en) | 2017-03-20 | 2021-03-09 | Raytheon Technologies Corporation | Combustor liner with gasket for gas turbine engine |
KR101872856B1 (ko) * | 2017-04-27 | 2018-07-02 | 연세대학교 산학협력단 | 다층 복합 충돌 및 유출 냉각이 가능한 중공 핀과 충돌 흡입 구조의 가스터빈 연소기 라이너 |
US10663168B2 (en) | 2017-08-02 | 2020-05-26 | Raytheon Technologies Corporation | End rail mate-face low pressure vortex minimization |
US11009230B2 (en) | 2018-02-06 | 2021-05-18 | Raytheon Technologies Corporation | Undercut combustor panel rail |
US11248791B2 (en) | 2018-02-06 | 2022-02-15 | Raytheon Technologies Corporation | Pull-plane effusion combustor panel |
US10830435B2 (en) | 2018-02-06 | 2020-11-10 | Raytheon Technologies Corporation | Diffusing hole for rail effusion |
US11022307B2 (en) * | 2018-02-22 | 2021-06-01 | Raytheon Technology Corporation | Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling |
DE102018212394B4 (de) | 2018-07-25 | 2024-03-28 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement |
US11073285B2 (en) * | 2019-06-21 | 2021-07-27 | Raytheon Technologies Corporation | Combustor panel configuration with skewed side walls |
CN112923398B (zh) * | 2021-03-04 | 2022-07-22 | 西北工业大学 | 一种加力燃烧室防振隔热屏 |
CN115930259A (zh) * | 2023-01-31 | 2023-04-07 | 上海电气燃气轮机有限公司 | 一种燃气轮机燃烧室的隔热瓦及热屏 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0224817B1 (de) * | 1985-12-02 | 1989-07-12 | Siemens Aktiengesellschaft | Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen |
US5216886A (en) * | 1991-08-14 | 1993-06-08 | The United States Of America As Represented By The Secretary Of The Air Force | Segmented cell wall liner for a combustion chamber |
GB2298266A (en) * | 1995-02-23 | 1996-08-28 | Rolls Royce Plc | A cooling arrangement for heat resistant tiles in a gas turbine engine combustor |
EP1005620B1 (de) * | 1997-08-18 | 2002-07-03 | Siemens Aktiengesellschaft | Hitzeschildkomponente mit kühlfluidrückführung |
US6470685B2 (en) * | 2000-04-14 | 2002-10-29 | Rolls-Royce Plc | Combustion apparatus |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB849255A (en) | 1956-11-01 | 1960-09-21 | Josef Cermak | Method of and arrangements for cooling the walls of combustion spaces and other spaces subject to high thermal stresses |
US4838030A (en) * | 1987-08-06 | 1989-06-13 | Avco Corporation | Combustion chamber liner having failure activated cooling and dectection system |
EP0539359B1 (de) * | 1990-07-17 | 1994-04-20 | Siemens Aktiengesellschaft | Rohrstück, insbesondere Flammrohr, mit gekühltem Stützrahmen für eine hitzefeste Auskleidung |
US5431020A (en) * | 1990-11-29 | 1995-07-11 | Siemens Aktiengesellschaft | Ceramic heat shield on a load-bearing structure |
US5435139A (en) * | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
FR2752916B1 (fr) | 1996-09-05 | 1998-10-02 | Snecma | Chemise de protection thermique pour chambre de combustion de turboreacteur |
WO1998013645A1 (de) | 1996-09-26 | 1998-04-02 | Siemens Aktiengesellschaft | Hitzeschildkomponente mit kühlfluidrückführung und hitzeschildanordnung für eine heissgasführende komponente |
US6397765B1 (en) * | 1998-03-19 | 2002-06-04 | Siemens Aktiengesellschaft | Wall segment for a combustion chamber and a combustion chamber |
DE19963371A1 (de) * | 1999-12-28 | 2001-07-12 | Alstom Power Schweiz Ag Baden | Gekühltes Hitzeschild |
US6606861B2 (en) * | 2001-02-26 | 2003-08-19 | United Technologies Corporation | Low emissions combustor for a gas turbine engine |
EP1284390A1 (de) * | 2001-06-27 | 2003-02-19 | Siemens Aktiengesellschaft | Hitzeschildanordnung für eine Heissgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
DE10214570A1 (de) * | 2002-04-02 | 2004-01-15 | Rolls-Royce Deutschland Ltd & Co Kg | Mischluftloch in Gasturbinenbrennkammer mit Brennkammerschindeln |
EP1443275B1 (de) * | 2003-01-29 | 2008-08-13 | Siemens Aktiengesellschaft | Brennkammer |
US7219498B2 (en) * | 2004-09-10 | 2007-05-22 | Honeywell International, Inc. | Waffled impingement effusion method |
-
2003
- 2003-08-13 EP EP03018415A patent/EP1507116A1/de not_active Withdrawn
-
2004
- 2004-07-20 CN CNA2004800216354A patent/CN1829879A/zh active Pending
- 2004-07-20 WO PCT/EP2004/008116 patent/WO2005019730A1/de active Application Filing
- 2004-07-20 EP EP04763361.5A patent/EP1654495B1/de not_active Expired - Lifetime
- 2004-07-20 JP JP2006522925A patent/JP4436837B2/ja not_active Expired - Fee Related
- 2004-07-20 US US10/568,115 patent/US7849694B2/en not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0224817B1 (de) * | 1985-12-02 | 1989-07-12 | Siemens Aktiengesellschaft | Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen |
US5216886A (en) * | 1991-08-14 | 1993-06-08 | The United States Of America As Represented By The Secretary Of The Air Force | Segmented cell wall liner for a combustion chamber |
GB2298266A (en) * | 1995-02-23 | 1996-08-28 | Rolls Royce Plc | A cooling arrangement for heat resistant tiles in a gas turbine engine combustor |
EP1005620B1 (de) * | 1997-08-18 | 2002-07-03 | Siemens Aktiengesellschaft | Hitzeschildkomponente mit kühlfluidrückführung |
US6470685B2 (en) * | 2000-04-14 | 2002-10-29 | Rolls-Royce Plc | Combustion apparatus |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100077764A1 (en) * | 2008-10-01 | 2010-04-01 | United Technologies Corporation | Structures with adaptive cooling |
US9587832B2 (en) * | 2008-10-01 | 2017-03-07 | United Technologies Corporation | Structures with adaptive cooling |
DE102015205975A1 (de) * | 2015-04-02 | 2016-10-06 | Siemens Aktiengesellschaft | Umführungs-Hitzeschildelement |
Also Published As
Publication number | Publication date |
---|---|
EP1654495A1 (de) | 2006-05-10 |
EP1507116A1 (de) | 2005-02-16 |
JP2007501927A (ja) | 2007-02-01 |
US7849694B2 (en) | 2010-12-14 |
JP4436837B2 (ja) | 2010-03-24 |
CN1829879A (zh) | 2006-09-06 |
EP1654495B1 (de) | 2017-04-12 |
US20090077974A1 (en) | 2009-03-26 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1654495B1 (de) | Hitzeschildanordnung für eine ein heissgas führende komponente, insbesondere für eine brennkammer einer gasturbine | |
EP1005620B1 (de) | Hitzeschildkomponente mit kühlfluidrückführung | |
EP0928396B1 (de) | Hitzeschildkomponente mit kühlfluidrückführung und hitzeschildanordnung für eine heissgasführende komponente | |
DE102005025823B4 (de) | Verfahren und Vorrichtung zum Kühlen einer Brennkammerauskleidung und eines Übergangsteils einer Gasturbine | |
DE60224339T2 (de) | Kühleinsatz mit tangentialer Ausströmung | |
EP0244693B1 (de) | Heissgasüberhitzungsschutzeinrichtung für Gasturbinentriebwerke | |
DE60221820T2 (de) | Prallanordnung für eine konvektive kühlung mit aussenluftzufuhr | |
DE60202212T2 (de) | Kühlbares segment für turbomaschinen und turbinen mit brennkammer | |
DE60027967T2 (de) | Turbinenschaufel mit thermisch isolierter Spitze | |
EP1636526A1 (de) | Brennkammer | |
EP2084368B1 (de) | Turbinenschaufel | |
DE102008002890A1 (de) | Wechselseitig gekühltes Turbinenleitrad | |
DE102005044183A1 (de) | Vorrichtung und Verfahren zur Kühlung von Turbinenschaufelplattformen | |
WO2006064038A1 (de) | Hitzeschildelement | |
EP3132202B1 (de) | Umführungs-hitzeschildelement | |
WO2014177371A1 (de) | Brennerlanze mit hitzeschild für einen brenner einer gasturbine | |
WO2013135859A2 (de) | Ringbrennkammer-bypass | |
EP1409926A1 (de) | Prallkühlvorrichtung | |
EP1510653B1 (de) | Gekühlte Turbinenschaufel | |
EP1165942B1 (de) | Strömungsmaschine mit einer kühlbaren anordnung von wandelementen und verfahren zur kühlung einer anordnung von wandelementen | |
EP2347100B1 (de) | Gasturbine mit kühleinsatz | |
WO2004109187A1 (de) | Hitzeschildelement | |
EP2270397A1 (de) | Gasturbinenbrennkammer und Gasturbine | |
DE102006010863A1 (de) | Turbomaschine, insbesondere Verdichter | |
EP2184449A1 (de) | Leitschaufelträger, und Gasturbine und Gas- bzw. Dampfturbinenanlage mit solchem Leitschaufelträger |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
WWE | Wipo information: entry into national phase |
Ref document number: 200480021635.4 Country of ref document: CN |
|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
DPEN | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed from 20040101) | ||
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
REEP | Request for entry into the european phase |
Ref document number: 2004763361 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2004763361 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2006522925 Country of ref document: JP |
|
WWP | Wipo information: published in national office |
Ref document number: 2004763361 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 10568115 Country of ref document: US |