EP1351021A2 - Chambre de combustion de turbine avec refroidissement initial par film fluide - Google Patents

Chambre de combustion de turbine avec refroidissement initial par film fluide Download PDF

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Publication number
EP1351021A2
EP1351021A2 EP03001783A EP03001783A EP1351021A2 EP 1351021 A2 EP1351021 A2 EP 1351021A2 EP 03001783 A EP03001783 A EP 03001783A EP 03001783 A EP03001783 A EP 03001783A EP 1351021 A2 EP1351021 A2 EP 1351021A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber according
starter film
openings
starter
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.)
Withdrawn
Application number
EP03001783A
Other languages
German (de)
English (en)
Other versions
EP1351021A3 (fr
Inventor
Miklos Dr.-Ing. Gerendas
Michael Ebel
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1351021A2 publication Critical patent/EP1351021A2/fr
Publication of EP1351021A3 publication Critical patent/EP1351021A3/fr
Withdrawn legal-status Critical Current

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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

Definitions

  • the invention relates to a combustion chamber of a gas turbine with starter film cooling of one combustion chamber wall for several circular burners.
  • the combustion chamber wall of a combustion chamber forms the wall of one Space in which fuel with the compressed by the compressor Air is burned before it is expanded in the turbine and doing work. Because the gas temperatures in the combustion chamber usually above the melting temperature of the material the combustion chamber wall, it must be cooled accordingly become. To achieve a long lifespan correspondingly low temperature values are observed.
  • the combustion chamber wall can be equipped with cooling rings (US 4,566,280), effusion bores (US 5,181,379), donated Shingles (EP 1 098 141 A1) or impact and effusion-cooled Shingles (US 5,435,139).
  • This starter film protects the wall until the actual cooling for the Combustion chamber wall shows enough effect.
  • the one for this starter film Air needed can come from within a cover and a base plate formed space or from one Annulus between the combustion chamber wall and a combustion chamber housing are fed.
  • the flow openings through the The combustion chamber wall is mostly circular, regularly distributed Holes of constant cross-section without chamfer or radius the inlet side.
  • the starter film is mostly parallel blown along the combustion chamber wall.
  • the air for the starter film is only on one side a component belonging to the combustion chamber wall, while them on the other side from a flow surface of the heat shield is limited.
  • the starter film is blown out of the combustion chamber wall, around this part of the combustion chamber from the hot gases of the To protect combustion. This is usually done through an evenly distributed number of circular holes without chamfer or radius on the inflow side on a certain pitch circle.
  • To even out the individual rays first be blown onto the back of the heat shield.
  • starter film At the Impact of the rays cool the heat shield and unite become a homogeneous film (starter film), which then flows along the combustion chamber wall.
  • starter film homogeneous film
  • the single-walled or with additional impact-cooled shingles can be executed first A protective cooling film for a certain distance downstream built up. Without such a starter film, the opening part would be the combustion chamber wall is not adequately protected.
  • the invention has for its object a combustion chamber to create the type mentioned above, which with a simple structure and easier, less expensive to manufacture an optimized Cooling and associated long life.
  • the object is characterized by the features of Main claim solved, the sub-claims show further advantageous Embodiments of the invention.
  • the combustion chamber according to the invention is characterized by a number significant benefits.
  • the temperature gradient drops the combustion chamber wall in the circumferential direction.
  • the take thermally induced voltages in the combustion chamber wall this drastically decreases, so that the service life at a given Temperature for a certain material increased significantly can be.
  • the operating temperature the combustion chamber with the same service life and increase the specified material.
  • Another advantage is that at the same temperature the combustion chamber wall and with the same service life weaker and / or cheaper material can be avoided can.
  • the starter film is thus in the circumferential direction the combustion chamber varies so that in the combustion chamber wall uniform temperature arises.
  • a number of maxima or minima that are the same can be the number of burners or an integer multiple the number of burners can be.
  • the flow openings for the passage of Cooling air and to form the starter film must be according to the invention not necessarily circular holes. Because these openings they can usually be cut with a laser take any shape. Also the cross section of the respective opening not at any point along the hole axis opening must be constant. According to the invention, it is crucial that a predetermined amount of air through this opening flows. This means that an opening with a certain Area and a certain flow coefficient provided is. In the case of irregular openings, the description of the Air volume to be carried out the equivalent or hydraulic Diameter used as a comparison value. To the following Simplifying the discussion and making it clearer will hereinafter referred to as openings or holes, respectively these do not necessarily have a circular cross section must have.
  • One way of varying the flow rate per circumferential length the combustion chamber can be done in that the equivalent diameter of the evenly distributed starter film holes is varied.
  • An alternative embodiment of the invention provides that with the same equivalent diameter of the starter film openings or holes the hole spacing is varied.
  • the variation in the amount of air in the starter film can be continuous be or refer to discrete states, for example two or reduce three. This is discussed below in conjunction with an embodiment will be explained in more detail.
  • the invention it is also possible to use the methods of variation the amount of air to form the starter film or for training to combine the respective maxima or minima. Also it is possible according to the invention between individual burners on a limited piece of the circumference of the combustion chamber wall to completely do without a starter film.
  • the invention can also provide for the variation the cooling by the starter film is not symmetrical train the respective burner axis, i.e. the maximum cooling exactly on the axis of symmetry of the burner and the minimal cooling to be placed exactly between the axes of symmetry. Because the maximum and minimal load on the combustion chamber wall is displaced in the circumferential direction by the burner swirl, it can be cheap, also the variation of the starter film thickness to shift accordingly in the circumferential direction. This will the strength of the starter film always on the locally necessary Quantity limited. This leads to a further saving of Cooling air, which is then used, for example, to reduce pollutant emissions be used in mixture preparation can.
  • Fig. 1 shows a section in schematic side view by a gas turbine combustion chamber according to the invention.
  • This includes a cover 1 of a combustion chamber head and a Base plate 2.
  • the reference numeral 4 is a combustion chamber wall shown in a schematically illustrated turbine guide vane 8 opens.
  • the reference number 10 shows a Combustion chamber outer casing, a combustion chamber inner casing is included provided with the reference number 11.
  • the reference number 7 shows a burner with a burner arm and swirl generator.
  • the gas turbine combustor also includes a heat shield 9 with a hole for the burner 7 as well as individual, later openings 6 to be described for forming a starter film 3.
  • the air for the starter film 3 from within the Cover 1 and the base plate 2 formed space or from the annulus between the combustion chamber wall and the combustion chamber housing 10, 11 supplied.
  • the air for the starter film 3rd only on one side by one belonging to the combustion chamber wall 4 Component guided, on the other side of a flow surface of the heat shield 5 limited.
  • the starter film 3 blown out around this part of the combustion chamber wall 4 to protect against the hot gases of combustion. This is usually done by an equally distributed number on circular bores without chamfer or radius on the Inflow side on a certain pitch circle.
  • the arrangement of the Prior art openings 6 are shown in Figure 3.
  • the reference numeral 14 the burner axis (line of symmetry of the burner) shows while the pitch circle of the starter film 3 is provided with the reference number 13.
  • the pitch circle the burner is illustrated by reference number 16.
  • the individual openings 6 have a distance x and a Diameter D on.
  • the openings are therefore circular bores without chamfer or radius on the inflow side on a certain pitch circle 13 arranged.
  • the individual can Air jets first on the back of the heat shield 5 be blown out. When the rays hit, they cool down the heat shield 5 and combine to form a homogeneous film, which then flows along the combustion chamber wall 4 (see Fig. 2).
  • the sub-areas of the starter film or the individual sub-circles are indicated by 13a and 13b.
  • the reference number 12 shows the further cooling of the combustion chamber wall 4 through effusion cooling.
  • the Combustion chamber wall 4 single-walled or with additionally impact-cooled Combustion chamber shingles.
  • Fig. 4 shows a first embodiment of the invention, in which initially, as in the following illustrations it can be seen that a line of symmetry 15 of the maximum Starter film in the circumferential direction to the line of symmetry of the burner 7 (burner axis 14) is offset.
  • FIG. 4 to 7 are also in the exemplary embodiments Pitch circles 13 of the starter film 3 are shown, as is the pitch circle 16 the burner 7.
  • the reference number 4 shows the inner one Combustion chamber wall, Figs. 4 to 7 are each in the direction of view B-B according to Fig. 2.
  • Fig. 6 shows another embodiment, in which the variation of the starter film 3 by differently assigned Pitch circles 13a and 13b.
  • Fig. 7 shows another embodiment, in which the starter film 3 by varying the contour K1 or K2 Openings 6 takes place.
  • contour K1 (detail K1) there is a chamfer or a radius of curvature b is provided.
  • K2 can also be designed without a chamfer or radius of curvature be provided.
  • moves the diameter varying on the circumference for example, in one Range of 0.5 - 5 mm, preferably 1 - 2.5 mm.
  • the most Scope varying ratio of center distance to diameter the openings 6 is preferably in a range of 1.5 - 10 mm, preferably 2 - 5 mm.
  • the width of the chamfer is, for example, in the range of 0-5 mm, preferably in the range of 0.5 - 2 mm.
  • the angle of the chamfer is, for example 15 ° - 75 °, preferably 30 ° to 60 °, ideally almost 45 °.
  • the entry radius is conveniently in one Range from 0 - 5 mm, preferably from 0.5 - 2 mm.
  • the variation can be continuous or refer to discrete states, e.g. reduce two or three.
  • the shift in starter film thickness in the circumferential direction can be, for example, 4 °, such as this is shown in Figs. 4 to 7.

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)
  • Combustion Of Fluid Fuel (AREA)
EP03001783A 2002-04-02 2003-01-28 Chambre de combustion de turbine avec refroidissement initial par film fluide Withdrawn EP1351021A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10214573 2002-04-02
DE10214573A DE10214573A1 (de) 2002-04-02 2002-04-02 Brennkammer einer Gasturbine mit Starterfilmkühlung

Publications (2)

Publication Number Publication Date
EP1351021A2 true EP1351021A2 (fr) 2003-10-08
EP1351021A3 EP1351021A3 (fr) 2005-01-19

Family

ID=27816107

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03001783A Withdrawn EP1351021A3 (fr) 2002-04-02 2003-01-28 Chambre de combustion de turbine avec refroidissement initial par film fluide

Country Status (3)

Country Link
US (1) US7124588B2 (fr)
EP (1) EP1351021A3 (fr)
DE (1) DE10214573A1 (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7614235B2 (en) * 2005-03-01 2009-11-10 United Technologies Corporation Combustor cooling hole pattern
US7451600B2 (en) * 2005-07-06 2008-11-18 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
EP2116770B1 (fr) * 2008-05-07 2013-12-04 Siemens Aktiengesellschaft Atténuation dynamique de chambre de combustion et agencement de refroidissement
US20100037622A1 (en) * 2008-08-18 2010-02-18 General Electric Company Contoured Impingement Sleeve Holes
US8091367B2 (en) * 2008-09-26 2012-01-10 Pratt & Whitney Canada Corp. Combustor with improved cooling holes arrangement
US8307657B2 (en) * 2009-03-10 2012-11-13 General Electric Company Combustor liner cooling system
DE102009033592A1 (de) 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Starterfilm zur Kühlung der Brennkammerwand
EP4242520A3 (fr) 2013-10-24 2023-11-01 RTX Corporation Chambre de combustion pour moteur de turbine à gaz avec agencement de jet de trempe
US10317080B2 (en) 2013-12-06 2019-06-11 United Technologies Corporation Co-swirl orientation of combustor effusion passages for gas turbine engine combustor
EP2886798B1 (fr) 2013-12-20 2018-10-24 Rolls-Royce Corporation Trous de refroidissement de film usinés mécaniquement
GB201715366D0 (en) 2017-09-22 2017-11-08 Rolls Royce Plc A combustion chamber
US11067003B2 (en) 2017-09-29 2021-07-20 General Electric Company Fluid cooling structure for an electric machine of a gas turbine engine
US10890327B2 (en) 2018-02-14 2021-01-12 General Electric Company Liner of a gas turbine engine combustor including dilution holes with airflow features
DE102018212394B4 (de) 2018-07-25 2024-03-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit Strömungsleiteinrichtung aufweisendem Wandelement
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US20240200778A1 (en) * 2022-12-20 2024-06-20 General Electric Company Gas turbine engine combustor with a set of dilution passages
US20240200777A1 (en) * 2022-12-20 2024-06-20 General Electric Company Gas turbine engine combustor with a set of dilution passages

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4566280A (en) 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US5181379A (en) 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
US5279127A (en) 1990-12-21 1994-01-18 General Electric Company Multi-hole film cooled combustor liner with slotted film starter
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
EP1098141A1 (fr) 1999-11-06 2001-05-09 Rolls-Royce Plc Eléments de paroi pour turbomachine

Family Cites Families (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL79375C (fr) * 1951-05-31
US4686823A (en) * 1986-04-28 1987-08-18 United Technologies Corporation Sliding joint for an annular combustor
GB2204672B (en) * 1987-05-06 1991-03-06 Rolls Royce Plc Combustor
US5012645A (en) * 1987-08-03 1991-05-07 United Technologies Corporation Combustor liner construction for gas turbine engine
US4916095A (en) * 1988-07-14 1990-04-10 The University Of Michigan Modified clay sorbents
GB2221979B (en) * 1988-08-17 1992-03-25 Rolls Royce Plc A combustion chamber for a gas turbine engine
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
US5161223A (en) * 1989-10-23 1992-11-03 International Business Machines Corporation Resumeable batch query for processing time consuming queries in an object oriented database management system
US5129231A (en) * 1990-03-12 1992-07-14 United Technologies Corporation Cooled combustor dome heatshield
GB9018013D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
GB9018014D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
US5142871A (en) * 1991-01-22 1992-09-01 General Electric Company Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures
US5241827A (en) * 1991-05-03 1993-09-07 General Electric Company Multi-hole film cooled combuster linear with differential cooling
GB9112324D0 (en) * 1991-06-07 1991-07-24 Rolls Royce Plc Gas turbine engine combustor
CA2070518C (fr) * 1991-07-01 2001-10-02 Adrian Mark Ablett Ensemble dome pour chambre de combustion
US5307637A (en) * 1992-07-09 1994-05-03 General Electric Company Angled multi-hole film cooled single wall combustor dome plate
US5261223A (en) * 1992-10-07 1993-11-16 General Electric Company Multi-hole film cooled combustor liner with rectangular film restarting holes
US5331805A (en) * 1993-04-22 1994-07-26 Alliedsignal Inc. Reduced diameter annular combustor
DE4427222A1 (de) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
DE19502328A1 (de) * 1995-01-26 1996-08-01 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
DE19508111A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
GB2299399A (en) * 1995-03-25 1996-10-02 Rolls Royce Plc Variable geometry air-fuel injector
FR2751731B1 (fr) * 1996-07-25 1998-09-04 Snecma Ensemble bol-deflecteur pour chambre de combustion de turbomachine
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
US6155056A (en) * 1998-06-04 2000-12-05 Pratt & Whitney Canada Corp. Cooling louver for annular gas turbine engine combustion chamber
US6474070B1 (en) * 1998-06-10 2002-11-05 General Electric Company Rich double dome combustor
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US6205789B1 (en) * 1998-11-13 2001-03-27 General Electric Company Multi-hole film cooled combuster liner
US6266961B1 (en) * 1999-10-14 2001-07-31 General Electric Company Film cooled combustor liner and method of making the same
US6260359B1 (en) * 1999-11-01 2001-07-17 General Electric Company Offset dilution combustor liner
GB2356924A (en) * 1999-12-01 2001-06-06 Abb Alstom Power Uk Ltd Cooling wall structure for combustor
US6434821B1 (en) * 1999-12-06 2002-08-20 General Electric Company Method of making a combustion chamber liner
US6735950B1 (en) * 2000-03-31 2004-05-18 General Electric Company Combustor dome plate and method of making the same
US6408629B1 (en) * 2000-10-03 2002-06-25 General Electric Company Combustor liner having preferentially angled cooling holes
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
US6655146B2 (en) * 2001-07-31 2003-12-02 General Electric Company Hybrid film cooled combustor liner
US6513331B1 (en) * 2001-08-21 2003-02-04 General Electric Company Preferential multihole combustor liner
US6871488B2 (en) * 2002-12-17 2005-03-29 Pratt & Whitney Canada Corp. Natural gas fuel nozzle for gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4566280A (en) 1983-03-23 1986-01-28 Burr Donald N Gas turbine engine combustor splash ring construction
US5181379A (en) 1990-11-15 1993-01-26 General Electric Company Gas turbine engine multi-hole film cooled combustor liner and method of manufacture
US5279127A (en) 1990-12-21 1994-01-18 General Electric Company Multi-hole film cooled combustor liner with slotted film starter
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
EP1098141A1 (fr) 1999-11-06 2001-05-09 Rolls-Royce Plc Eléments de paroi pour turbomachine

Also Published As

Publication number Publication date
US7124588B2 (en) 2006-10-24
EP1351021A3 (fr) 2005-01-19
US20030182943A1 (en) 2003-10-02
DE10214573A1 (de) 2003-10-16

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