DE19528406A1 - Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension - Google Patents

Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension

Info

Publication number
DE19528406A1
DE19528406A1 DE1995128406 DE19528406A DE19528406A1 DE 19528406 A1 DE19528406 A1 DE 19528406A1 DE 1995128406 DE1995128406 DE 1995128406 DE 19528406 A DE19528406 A DE 19528406A DE 19528406 A1 DE19528406 A1 DE 19528406A1
Authority
DE
Germany
Prior art keywords
combustion chamber
raster
ports
air transfer
air
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Withdrawn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
DE1995128406
Other languages
German (de)
Inventor
William Kwan
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
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Priority to DE1995128406 priority Critical patent/DE19528406A1/en
Publication of DE19528406A1 publication Critical patent/DE19528406A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0025—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply
    • F15D1/003—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/02—Influencing flow of fluids in pipes or conduits
    • F15D1/06—Influencing flow of fluids in pipes or conduits by influencing the boundary layer
    • 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
    • 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

Abstract

The exterior of the wall is regularly roughened upstream of the hole inlets. This is preferably done in a raster pattern to give a roughness 0.2 and 1 mm in height. The pattern is applied by shot blasting or rolling. Thus cross-rolling gives rise to a fluted design eminently suitable for gas turbines.

Description

Die Erfindung betrifft eine luftumströmte Gasturbinen-Brennkammer mit einer Vielzahl von Luftübertrittsöffnungen in einer sich im wesentlichen in Luftan­ strömrichtung erstreckenden Brennkammer-Wand, wobei die Luftübertritts­ öffnungen als in Anströmrichtung geneigt verlaufende Bohrungen ausgebil­ det sind.The invention relates to a gas turbine combustion chamber with an air flow Variety of air vents in an essentially air flow direction extending combustion chamber wall, the air transfer openings formed as bores inclined in the direction of flow det.

Bekannt ist eine derartige Brennkammer-Wand aus der DE 39 24 473 A1. Dabei dienen die Luftübertrittsöffnungen insbesondere als Kühlluft-Bohrun­ gen zur wirksamen Filmkühlung der Brennkammer-Wand. Wenngleich mit dieser bekannten Anordnung eine ausreichende Kühlwirkung erzielbar sein kann, so kann es dennoch wünschenswert sein, vermehrt Luft über die ge­ neigten Luftübertrittsöffnungen in den Innenraum der Brennkammer zu lei­ ten, die dann dort als Zumischluft für eine verbesserte Verbrennung sorgt.Such a combustion chamber wall is known from DE 39 24 473 A1. The air transfer openings serve in particular as a cooling air bore conditions for effective film cooling of the combustion chamber wall. Although with a sufficient cooling effect can be achieved in this known arrangement can, it may still be desirable, increased air over the ge air transfer openings tended to lead into the interior of the combustion chamber ten, which then, as admixed air, ensures improved combustion.

Maßnahmen aufzuzeigen, mit Hilfe derer der Luftmassenstrom über die Luftübertrittsöffnungen einfach und effizient verstärkt werden kann, ist dem­ nach Aufgabe der vorliegenden Erfindung. Show measures with the help of which the air mass flow over the Air vents can be easily and efficiently reinforced according to the object of the present invention.  

Zur Lösung dieser Aufgabe ist vorgesehen, daß die Wand-Außenseite stromauf der Bohrungsmündungen ein Rauhigkeits-Muster aufweist. Vorteil­ hafte Aus- und Weiterbildungen sind Inhalt der Unteransprüche.To solve this problem it is provided that the outside of the wall has a roughness pattern upstream of the bore mouths. Advantage Strong training and further education are the content of the subclaims.

Rauhigkeiten im weitesten Sinne an Brennkammer-Außenwänden sind grundsätzlich bekannt. Verwiesen wird hierzu beispielshalber auf die US 4 392 355, wonach die Innenwände eines kühlluftführenden Schlitzes mit einer gezielten Rauhigkeit versehen sind, um die Filmkühlung insbesondere die­ ser Wandabschnitte zu verbessern. Einen anderen Zweck verfolgt jedoch das Rauhigkeits-Muster nach der vorliegenden Erfindung. Erfindungsgemäß erzeugt nämlich dieses Rauhigkeits-Muster stromauf der Bohrungsmündun­ gen Turbulenzen in der ansonsten im wesentlichen laminar an der Brenn­ kammer-Außenwand vorbeistreichenden Luftströmung, wodurch ein ver­ mehrter Anteil dieser Luftströmung in die Bohrungen bzw. Luftübertrittsöff­ nungen hineingelangen kann. Ein ähnliches Prinzip verfolgt zwar auch eine Brennkammerausbildung nach der US 4 269 032, jedoch verlaufen dort zum einen die Luftübertrittsöffnungen senkrecht zur Brennkammer-Wand und somit auch im wesentlichen senkrecht zur Luftanströmrichtung, zum anderen ist dort eine quasi überdimensionale Rauhigkeit in Form von Luftleitstegen vorgesehen.Roughness in the broadest sense are on the outer walls of the combustion chamber basically known. For this purpose, reference is made, for example, to US 4,392,355. after which the inner walls of a cooling air-carrying slot with a targeted roughness are provided in order to cool the film in particular to improve these wall sections. But it has another purpose the roughness pattern according to the present invention. According to the invention namely creates this roughness pattern upstream of the bore mouth against turbulence in the otherwise essentially laminar at the focal point Chamber outer wall passing air flow, creating a ver more of this air flow into the holes or air transfer opening can get into it. A similar principle follows one Combustion chamber training according to US 4,269,032, however, run there to one the air transfer openings perpendicular to the combustion chamber wall and thus also essentially perpendicular to the air flow direction, to the other there is a quasi-oversized roughness in the form of air guide bars intended.

In einer bevorzugten Ausführungsform kann das Rauhigkeits-Muster raster­ artig ausgebildet sein. Ein derartiges Raster kann dabei direkt stromauf jeder Bohrungsmündung vorgesehen sein, es ist jedoch auch möglich, einer Gruppe von Bohrungen bzw. Luftübertrittsöffnungen ein gemeinsames Rau­ higkeits-Muster beispielsweise in Rasterform zuzuordnen. Die bevorzugte Höhe der Rauhigkeit liegt im Bereich von 0,2 mm bis 1 mm, da sich hiermit eine optimale Wirbelbildung zur Vergrößerung des in die Luftübertrittsöff­ nungen eintretenden Luftmassenstromes einstellt. Auf einfache Weise er­ zeugt werden kann die Rauhigkeit bzw. das Rauhigkeits-Muster durch Kugelstrahlen oder durch Aufrollen. Ein kreuzweises Aufrollen ergibt eine Riffelung, die sich als besonders vorteilhaft herausgestellt hat.In a preferred embodiment, the roughness pattern can raster be well-trained. Such a grid can be directly upstream of everyone Hole mouth may be provided, but it is also possible to one Group of holes or air transfer openings a common rough ability to assign patterns, for example in grid form. The preferred The height of the roughness is in the range of 0.2 mm to 1 mm, since this an optimal vortex formation to enlarge the in the air transfer opening sets incoming air mass flow. In a simple way The roughness or the roughness pattern can be produced by  Shot peening or by rolling up. Crosswise rolling up results in one Corrugation, which has proven to be particularly advantageous.

Claims (4)

1. Luftumströmte Gasturbinen-Brennkammer mit einer Vielzahl von Luftübertrittsöffnungen in einer sich im wesentlichen in Luftanström­ richtung erstreckenden Brennkammer-Wand, wobei die Luftüber­ trittsöffnungen als in Anströmrichtung geneigt verlaufende Bohrungen ausgebildet sind, dadurch gekennzeichnet, daß die Wand-Außenseite stromauf der Bohrungsmündungen ein Rauhigkeits-Muster aufweist.1. Air-circulating gas turbine combustion chamber with a plurality of air transfer openings in a combustion chamber wall extending essentially in the air inflow direction, the air transfer openings being designed as bores which are inclined in the flow direction, characterized in that the wall outside upstream of the bore openings has a roughness Pattern. 2. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß das Rauhigkeits-Muster rasterartig ausgebildet ist.2. combustion chamber according to claim 1, characterized in that the roughness pattern is grid-like is trained. 3. Brennkammer nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Höhe der Rauhigkeit im Bereich von 0,2 mm bis 1 mm liegt.3. combustion chamber according to claim 1 or 2, characterized in that the level of roughness in the area from 0.2 mm to 1 mm. 4. Brennkammer nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Rauhigkeit durch Kugelstrahlen oder durch Aufrollen erzeugt ist.4. combustion chamber according to one of claims 1 to 3, characterized in that the roughness by shot peening or generated by rolling up.
DE1995128406 1995-08-02 1995-08-02 Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension Withdrawn DE19528406A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE1995128406 DE19528406A1 (en) 1995-08-02 1995-08-02 Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE1995128406 DE19528406A1 (en) 1995-08-02 1995-08-02 Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension

Publications (1)

Publication Number Publication Date
DE19528406A1 true DE19528406A1 (en) 1997-02-06

Family

ID=7768522

Family Applications (1)

Application Number Title Priority Date Filing Date
DE1995128406 Withdrawn DE19528406A1 (en) 1995-08-02 1995-08-02 Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension

Country Status (1)

Country Link
DE (1) DE19528406A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130233349A1 (en) * 2012-03-06 2013-09-12 General Electric Company Systems and Methods to Clean Gas Turbine Fuel Chamber Components

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658339A (en) * 1950-11-29 1953-11-10 Lucas Ltd Joseph Sheet metal combustion chamber, flame tube, and the like
US2694357A (en) * 1950-07-18 1954-11-16 Chance Vought Aircraft Inc Boundary layer energization for flush inlets
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
DE2844349A1 (en) * 1977-10-11 1979-04-12 Snecma COMBUSTION DEVICE FOR TURBO ENGINE
DE3034321A1 (en) * 1979-02-13 1981-03-26 A Malmstroem Surface structure of a surface adapted for movement relative to a fluid
US4696442A (en) * 1986-07-14 1987-09-29 The Boeing Company Vortex generators for inlets
DE4142413C2 (en) * 1991-11-08 1993-12-09 Bmw Rolls Royce Gmbh Combustion chamber housing of a gas turbine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2694357A (en) * 1950-07-18 1954-11-16 Chance Vought Aircraft Inc Boundary layer energization for flush inlets
US2658339A (en) * 1950-11-29 1953-11-10 Lucas Ltd Joseph Sheet metal combustion chamber, flame tube, and the like
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
DE2844349A1 (en) * 1977-10-11 1979-04-12 Snecma COMBUSTION DEVICE FOR TURBO ENGINE
DE2844349C2 (en) * 1977-10-11 1986-07-17 Société Nationale d'Etude et de Construction de Moteurs d'Aviation, Paris Post-combustion duct for a jet engine
DE3034321A1 (en) * 1979-02-13 1981-03-26 A Malmstroem Surface structure of a surface adapted for movement relative to a fluid
US4696442A (en) * 1986-07-14 1987-09-29 The Boeing Company Vortex generators for inlets
DE4142413C2 (en) * 1991-11-08 1993-12-09 Bmw Rolls Royce Gmbh Combustion chamber housing of a gas turbine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
HAN,J.C., et.al.: Influence of Surface Heat Ratio on Heat Transfer Augmentation in Square Channels with Parallel, Crossed and V-Shaped Angled Ribs. In: ASME-Paper 91-GT-3, Orlando, FL June 3-6, 1991, S.1-9 *
LAU,S.C., et.al.: Effects of V-shaped rib arrays on turbulent heat transfer and friction of fully developed flow in a square channel. In: Int. J. Heat Mass Transfer., Vol.34, No.7, 1991, S.1605- S.1616 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130233349A1 (en) * 2012-03-06 2013-09-12 General Electric Company Systems and Methods to Clean Gas Turbine Fuel Chamber Components
CN103302597A (en) * 2012-03-06 2013-09-18 通用电气公司 Systems and methods to clean gas turbine fuel chamber components

Similar Documents

Publication Publication Date Title
DE4441507C2 (en) Cooled turbine blade
DE10127084B4 (en) Heat exchanger, in particular for motor vehicles
DE69630190T2 (en) MUFFLER DEVICE FOR INTERNAL COMBUSTION ENGINE
DE1476796C3 (en) A component of a gas turbine system made integrally from a high-strength material
DE69626592T2 (en) Muffler for air cooling system
DE4116886C2 (en) Perforated sheet metal as a heat shield
EP1705430B1 (en) Extracting hood with grease filter
DE102010060286A1 (en) Combustor device for a gas turbine, with improved cooling
DE2404297A1 (en) COOLING SYSTEM FOR IMPACT CONVECTION COOLING
DE1092255B (en) Method for cooling machine parts, in particular hollow gas turbine blades
DE10100241A1 (en) Heat exchanger tube for liquid or gaseous media
EP1959096B1 (en) Method for impingement cooling for gas turbines
WO2016030289A1 (en) Turbine blade
DE19629191C2 (en) Process for cooling a gas turbine
DE19911850B4 (en) Method and device for delimiting, detecting and extracting pollutants, in particular for extractor hoods
EP0602384A1 (en) Gasturbine combustor
DE4129598A1 (en) METHOD AND DEVICE FOR INCREASING THE HEAT TRANSFER BETWEEN A WALL AND A HEAT TRANSFER FLUID
DE19528406A1 (en) Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension
DE10143153A1 (en) Turbine blade for a gas turbine with at least one cooling recess
DE4311439C2 (en) Device for cleaning, humidifying, dehumidifying and tempering gas, primarily air
DE4142413C2 (en) Combustion chamber housing of a gas turbine
DE1068513B (en) Internal combustion engine with exhaust gas turbocharging
DE4101709C1 (en) Sound absorber for corrosive gas blower - is in form of massive, rigid glass body
DE3208640A1 (en) NOISE SHOCK ABSORBER FOR BOILER
DE102018105828A1 (en) Device for expanding an air volume flow

Legal Events

Date Code Title Description
OM8 Search report available as to paragraph 43 lit. 1 sentence 1 patent law
8127 New person/name/address of the applicant

Owner name: ROLLS-ROYCE DEUTSCHLAND GMBH, 61440 OBERURSEL, DE

8127 New person/name/address of the applicant

Owner name: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, 15827 DAHLEWI

8130 Withdrawal