EP0859127A1 - Kühlluftführung in einer Turbinen-Laufradscheibe - Google Patents
Kühlluftführung in einer Turbinen-Laufradscheibe Download PDFInfo
- Publication number
- EP0859127A1 EP0859127A1 EP98101045A EP98101045A EP0859127A1 EP 0859127 A1 EP0859127 A1 EP 0859127A1 EP 98101045 A EP98101045 A EP 98101045A EP 98101045 A EP98101045 A EP 98101045A EP 0859127 A1 EP0859127 A1 EP 0859127A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling air
- disc
- disk
- duct
- channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
Definitions
- the invention relates to a turbine impeller disk with disk fingers formed disc grooves for receiving turbine blades, as well as with Measures for guiding a cooling air flow from one in front of the pane into a room behind the window.
- the technical environment becomes In addition to DE 29 47 521 A1, reference is made in particular to DE 34 44 586 A1.
- a cooling air duct opening into the groove bottom of the disc groove can not arbitrarily with regard to its cross-sectional area be designed large, since the spatial Fields of the individual stress concentrations for the circumferential stresses superimpose and cause locally excessive voltage amplitudes can what is undesirable in terms of fatigue strength is.
- the object of the present invention is to show remedial measures for these problems.
- the solution to this problem is characterized in that at least in some of the disk fingers there is a cooling air skimming channel which starts from the front disk front side and which merges into a cooling air blow-out channel which likewise runs essentially in a radial direction in the disk finger and whose mouth opening is on the rear disk front side is closer to the disk axis than the disk ring section which has the disk grooves and is widened in the disk axis direction.
- Advantageous training and further education are included in the subclaims.
- At least one separate cooling air blow-out channel is in the
- the first turbine impeller disk is provided, via which the second, for example, arranged behind the first wheel disc Turbine impeller disk is supplied with cooling air.
- This cooling air exhaust duct runs in the first turbine impeller disk, for example at least partially in a disc finger of this impeller and is thereby by a cooling air skim, which also is at least partially provided in the corresponding disc finger with Cooling air supplied.
- This cooling air skimming duct receives the cooling air flow while from the space in front of the front window face, while the cooling air blow-out channel then this cooling air flow in the behind the Promotes disc lying space.
- this cooling air discharge channel is closer to the disc axis than that the disc grooves and, as usual, in the disc axis direction widened disc ring section is also no mixing of the cooling air flow with the working gas flow passed between the turbine blades to fear.
- cooling air skim there is usually a single cooling air skim and a single cooling air exhaust duct may not be sufficient, so preferred several such channels are provided, each in one Disc finger.
- this cooling air channels to promote or guide a cooling air flow from one in front of the turbine impeller disc to one behind the disc lying space in the disc fingers is provided by this Cooling channel system of course no weakening in the bottom of the groove To fear disk grooves. Rather, according to the invention, for example cooling air required for a second turbine impeller disk through the described cooling air ducts, namely the skimming duct and the blow-out channel is guided around the disk grooves.
- Reference number 1 denotes an impeller disk of a gas turbine, which carries a large number of turbine blades 2 as usual.
- Figures 2 and 4 one also recognizes a likewise usual closing plate 6, which is a turbine blade 2 secures in the corresponding disk groove 4.
- the turbine blades 2 are air-cooled, i.e. inside each turbine blade 2, a cooling channel system 7 is provided, which by a Cooling air duct 8, the inside of the impeller 1 from the front Front 1a leads to the groove bottom of the disk groove 4, supplied with cooling air becomes.
- space 9a the one in front of the disc 1 is significantly closer to the disc axis 3 lies, as the turbine blades 2 is thus - at least opposite the working gas passed between the turbine blades 2 relatively cool air flow.
- cooling air blow-out channel 10 provided by one with the Room 9a communicating with cooling air skimming duct 11
- Cooling air flow is supplied, both the cooling air skim 11 and also the cooling air exhaust duct 10 at least partially within one Disc fingers 5 run.
- These cooling air channels 10 and 11 thus open not in the disc groove 4, but are in the disc fingers 5 on the Disk groove 4 passed. A weakening of the bottom of the groove Disc groove 4 can therefore not occur through these cooling air channels 10 and 11.
- the cooling air discharge duct 10 in the disc finger 5 is essentially radial Direction, almost goes from the tip area 5 'of the disc finger 5 and lies closer with its mouth opening 10a to space 9b the disc axis 3, as that having the disc grooves 4, in the disc axis direction widened disc ring section 1 '. This ensures that the cooling air flow in space 9b does not coincide with that between mixed the working gas stream passed through the turbine blades 2.
- the end of the cooling air discharge channel 10 opposite the opening 10a is connected to a so-called channel channel 12, into which the cooling air skimming channel 11 opens.
- the inlet opening 11a of the cooling air skimming duct 11 on the front pane front side 1a is approximately at the same height as the outlet opening 10a of the blow-out duct 10, that is to say the inlet opening 11a likewise lies in an area in the space 9a in which a relatively cold air flow can be found .
- the cooling air duct via the duct system described, namely at least via a skimming duct 11 in the radial direction outwards, then via the duct groove 12 and finally via the blow-out duct 10 again essentially in the radial direction inwards is not only with regard to the existing pressure conditions, but also Also particularly advantageous from a manufacturing point of view.
- the skimming duct 11 open directly into the blow-out duct 10, on the one hand the angle of inclination of these two ducts 10, 11 would be unfavorable and the disk 1 would also be weakened unfavorably by these ducts.
- This connection of the blow-out channel 10 with the skimming channel 11 via the channel channel 12 is also advantageous in that this channel channel 12 runs in the tip region 5 'of the disc finger 5 and can thus be open in the radial direction to the outside, ie this can actually be an act in the tip area 5 'milled groove running in the direction of the disc axis 3.
- this side of the channel groove 12, which is open in the radial direction to the outside must be covered in order to achieve the desired cooling air guidance, which is why a so-called cover plate 13 is provided here.
- This cover plate 13 thus delimits the channel groove 12 in the radial direction to the outside and can thereby be form-fitting be fixed between two turbine blades 2 and by the closing plates 6 also securing these turbine blades 2.
- the cooling air skimming channel runs 11 in the tip area 5 'of the disc finger 5 substantially parallel to Disc axis 3 and is itself designed as a channel groove 12, the side open again in the radial direction with a cover plate 13 is covered.
- the design of this channel channel 12 in the embodiment 4 is thus similar to that in the embodiment according to Figure 2.
- the cooling air to be introduced into space 9b is one has the lowest possible total temperature in the rotating system Room 9a in front of the inlet opening 11a the air through this swirl nozzle 14 so highly swirling or with such a high peripheral speed, that the static pressure ratio between the area in front of this Inlet opening 11a and that passed between the turbine blades 2 Working gas flow just a penetration of the working gases in this Area in front of the entry opening 11a successfully prevented.
- This ensures that the relative total inlet temperature according to the thermodynamic process control reached a minimum.
- the guided cooling air experiences a reduction in the peripheral speed according to the change in the orbital radius. Because it it is a largely adiabatic process, the In the case of said overcurrent process, cooling air even works on the turbine impeller disk 1 from.
- the exemplary embodiment according to FIG. 2 is also analogous to the exemplary embodiment 4, the cover plate 13, inter alia, by the closing plate 6 positively fixed. Furthermore, here the cover plate 13 in its End area facing the inlet opening 11a, a so-called catch apron 13 'on the inlet or inlet cross-section of the skimming channel 11 certainly.
- the fact that the determining flow cross section for the in the cooling air mass flow entering space 9b from a separate one and replaceable part, namely the cover plate 13 with the defining Apron 13 'is formed, can - at least to a certain extent secondary turbine air system while maintaining the main components, namely in particular the impeller discs 1 quickly and inexpensively be varied and optimized.
- an impeller disk 1 according to the invention is distinguished inter alia from the fact that a cooling air flow from space 9a in front of front end face 1a in a space 9b behind the rear end face 1b can be performed without thereby the area of the disk grooves 4th and in particular the groove bottom is weakened. Rather, that is shown Channel system with one, several or all disc fingers 5 skimming channel 11 and blow-out channel 10 in view to the tension load on the impeller disk 1 in the area of the disk grooves 4 even more advantageous since the impeller 1 in the area of this Disc grooves 4 through the cooling air in the duct system additionally is cooled. Voltage peaks caused by an uneven Temperature distribution in the disc 1 are thus caused avoided or reduced.
- Cooling air channels 8, 10 and 11 can be designed as desired, i.e. the respective requirements be correspondingly circular, elliptical or otherwise shaped.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Lösung dieser Aufgabe ist dadurch gekennzeichnet, daß zumindest in einigen der Scheibenfinger jeweils ein von der vorderen Scheibenstirnseite ausgehender Kühlluft-Abschöpfkanal vorgesehen ist, welcher in einen ebenfalls im Scheibenfinger im wesentlichen in radialer Richtung verlaufenden Kühlluft-Ausblasekanal übergeht, dessen Mündungsöffnung auf der hinteren Scheibenstirnseite näher zur Scheibenachse liegt, als der die Scheibennuten aufweisende, in Scheibenachs-Richtung verbreiterte Scheibenringabschnitt. Vorteilhatte Aus- und Weiterbildungen sind Inhalt der Unteransprüche.
- Figur 1
- einen Teil-Längsschnitt durch eine Scheibennut einer Turbinen-Laufradscheibe zeigt, während in
- Figur 2
- ein vergleichbarer Teil-Längsschnitt durch einen Scheibenfinger dargestellt ist.
- Figur 3
- zeigt den Schnitt A-A aus Figur 2 und
- Figur 4
- zeigt ein anderes Ausführungsbeispiel in einer Figur 2 entsprechenden Darstellung.
Vorteilhaft ist diese Verbindung des Ausblasekanales 10 mit dem Abschöpfkanal 11 über die Kanalrinne 12 auch insofern, als diese Kanalrinne 12 im Spitzenbereich 5' des Scheibenfingers 5 verläuft und somit in radialer Richtung nach außen hin offen sein kann, d.h. es kann sich hierbei um eine tatsächlich in den Spitzenbereich 5' eingefräste, in Richtung der Scheibenachse 3 verlaufende Rinne handeln. Selbstverständlich muß diese in radialer Richtung nach außen offene Seite der Kanalrinne 12 abgedeckt sein, um die gewünschte Kühlluftführung zu erreichen, weshalb hier eine sog. Deckplatte 13 vorgesehen ist Diese Deckplatte 13 begrenzt somit die Kanalrinne 12 in radialer Richtung nach außen hin und kann dabei formschlüssig zwischen zwei Turbinenschaufeln 2 sowie durch die auch diese Turbinenschaufeln 2 sichernden Schließplatten 6 fixiert sein.
Claims (8)
- Turbinen-Laufradscheibe mit von Scheibenfingern (5) gebildeten Scheibennuten (4) zur Aufnahme von Turbinenschaufeln (2), sowie mit Maßnahmen zur Führung eines Kühlluftstromes von einem vor der Scheibe in einen hinter der Scheibe liegenden Raum (9a,9b),
dadurch gekennzeichnet, daß zumindest in einigen der Scheibenfinger (5) jeweils ein von der vorderen Scheibenstirnseite (1a) ausgehender Kühlluft-Abschöpfkanal (11) vorgesehen ist, welcher in einen ebenfalls im Scheibenfinger (5) im wesentlichen in radialer Richtung verlaufenden Kühlluft-Ausblasekanal (10) übergeht, dessen Mündungsöffnung (10a) auf der hinteren Scheibenstirnseite (1b) näher zur Scheibenachse (3) liegt, als der die Scheibennuten (4) aufweisende, in Scheibenachs-Richtung verbreiterte Scheibenringabschnitt (1'). - Turbinen-Laufradscheibe nach Anspruch 1,
dadurch gekennzeichnet, daß der im wesentlichen in radialer Richtung verlaufende Kühlluft-Abschöpfkanal (11) mit seiner Eintrittsöffnung (11a) auf der vorderen Scheibenstirnseite (1a) in etwa auf der gleichen Höhe mündet wie der Kühlluft-Ausblasekanal (10) auf der hinteren Scheibenstirnseite (1b). - Turbinen-Laufradscheibe nach Anspruch 2,
dadurch gekennzeichnet, daß der Kühlluft-Abschöpfkanal (11) und der Kühlluft-Ausblasekanal (10) über eine im Spitzenbereich (5') des Scheibenfingers (5) im wesentlichen parallel zur Scheibenachse (3) verlaufende Kanalrinne (12), deren in radialer Richtung nach außen offene Seite mit einer Deckplatte (13) abgedeckt ist, miteinander verbunden sind. - Turbinen-Laufradscheibe nach Anspruch 1,
dadurch gekennzeichnet, daß der Kühlluft-Abschöpfkanal (11) im Spitzenbereich (5') des Scheibenfingers (5) im wesentlichen parallel zur Scheibenachse (3) verläuft, und daß in Scheiben-Achsrichtung vor dem Scheiben-Kopfbereich (1'') zumindest eine Dralldüse (14) für die Zufuhr von Kühlluft vorgesehen ist. - Turbinen-Laufradscheibe nach Anspruch 4,
dadurch gekennzeichnet, daß der Kühlluft-Abschöpfkanal (11) als Kanalrinne (12) ausgebildet ist, deren in radialer Richtung nach außen offene Seite mit einer Deckplatte (13) abgedeckt ist. - Turbinen-Laufradscheibe nach Anspruch 5,
dadurch gekennzeichnet, daß die Deckplatte (13) eine den Einlauf des Abschöpfkanales (11) bestimmende Fangschürze (13') aufweist. - Turbinen-Laufradscheibe nach einem der vorangegangenen Ansprüche,
dadurch gekennzeichnet, daß die Deckplatten (13) formschlüssig zwischen den Turbinenschaufeln (2) durch die auch diese Turbinenschaufeln (2) sichernde Schließplatte (6) fixiert ist. - Turbinen-Laufradscheibe nach einem der vorangegangenen Ansprüche,
dadurch gekennzeichnet, daß weitere von der vorderen Scheibenstirnseite (1a) ausgehende Kühlluftkanäle (8) in den Scheibennuten (4) münden.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19705441A DE19705441A1 (de) | 1997-02-13 | 1997-02-13 | Turbinen-Laufradscheibe |
DE19705441 | 1997-02-13 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0859127A1 true EP0859127A1 (de) | 1998-08-19 |
EP0859127B1 EP0859127B1 (de) | 2000-06-14 |
Family
ID=7820089
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98101045A Expired - Lifetime EP0859127B1 (de) | 1997-02-13 | 1998-01-22 | Kühlluftführung in einer Turbinen-Laufradscheibe |
Country Status (3)
Country | Link |
---|---|
US (1) | US5957660A (de) |
EP (1) | EP0859127B1 (de) |
DE (2) | DE19705441A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1705339A2 (de) * | 2005-03-23 | 2006-09-27 | ALSTOM Technology Ltd | Rotorwelle, insbesondere für eine Gasturbine |
FR2981132A1 (fr) * | 2011-10-10 | 2013-04-12 | Snecma | Ensemble pour turbomachine a refroidissement de disque |
Families Citing this family (20)
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US7238008B2 (en) * | 2004-05-28 | 2007-07-03 | General Electric Company | Turbine blade retainer seal |
GB0513468D0 (en) * | 2005-07-01 | 2005-08-10 | Rolls Royce Plc | A mounting arrangement for turbine blades |
US8128365B2 (en) * | 2007-07-09 | 2012-03-06 | Siemens Energy, Inc. | Turbine airfoil cooling system with rotor impingement cooling |
CH699996A1 (de) * | 2008-11-19 | 2010-05-31 | Alstom Technology Ltd | Verfahren zum bearbeiten eines gasturbinenläufers. |
EP2233692A1 (de) * | 2009-03-27 | 2010-09-29 | Siemens Aktiengesellschaft | Axialturbomaschinenrotor mit Schaufelkühlung |
DE102009030353B3 (de) | 2009-06-22 | 2010-12-02 | Hofsaess, Marcel P. | Kappe für einen temperaturabhängigen Schalter sowie Verfahren zur Fertigung eines temperaturabhängigen Schalters |
DE102009039948A1 (de) | 2009-08-27 | 2011-03-03 | Hofsaess, Marcel P. | Temperaturabhängiger Schalter |
GB201016597D0 (en) | 2010-10-04 | 2010-11-17 | Rolls Royce Plc | Turbine disc cooling arrangement |
EP2453108B1 (de) * | 2010-11-15 | 2016-04-20 | MTU Aero Engines GmbH | Rotor für eine Strömungsmaschine |
US9133855B2 (en) * | 2010-11-15 | 2015-09-15 | Mtu Aero Engines Gmbh | Rotor for a turbo machine |
GB201020418D0 (en) * | 2010-12-02 | 2011-01-19 | Rolls Royce Plc | Fluid impingement arrangement |
US8622701B1 (en) * | 2011-04-21 | 2014-01-07 | Florida Turbine Technologies, Inc. | Turbine blade platform with impingement cooling |
US9068461B2 (en) * | 2011-08-18 | 2015-06-30 | Siemens Aktiengesellschaft | Turbine rotor disk inlet orifice for a turbine engine |
EP2725191B1 (de) * | 2012-10-23 | 2016-03-16 | Alstom Technology Ltd | Gasturbine und Turbinenschaufel für solch eine Gasturbine |
WO2015112226A2 (en) * | 2013-12-19 | 2015-07-30 | United Technologies Corporation | Blade feature to support segmented coverplate |
US10107102B2 (en) | 2014-09-29 | 2018-10-23 | United Technologies Corporation | Rotor disk assembly for a gas turbine engine |
US10458242B2 (en) * | 2016-10-25 | 2019-10-29 | Pratt & Whitney Canada Corp. | Rotor disc with passages |
KR102028804B1 (ko) * | 2017-10-19 | 2019-10-04 | 두산중공업 주식회사 | 가스 터빈 디스크 |
FR3085420B1 (fr) * | 2018-09-04 | 2020-11-13 | Safran Aircraft Engines | Disque de rotor avec arret axial des aubes, ensemble d'un disque et d'un anneau et turbomachine |
US11674395B2 (en) | 2020-09-17 | 2023-06-13 | General Electric Company | Turbomachine rotor disk with internal bore cavity |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
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DE573481C (de) * | 1930-03-23 | 1933-04-01 | Heinrich Ziegler | Gasturbine mit Hohlschaufeln |
US2447292A (en) * | 1943-10-12 | 1948-08-17 | Joseph E Van Acker | Gas-actuated turbine-driven compressor |
GB765225A (en) * | 1954-02-18 | 1957-01-09 | Parsons & Marine Eng Turbine | Improvements in and relating to the cooling of gas turbine blades and rotors |
GB801689A (en) * | 1954-09-10 | 1958-09-17 | Henschel & Sohn Ges Mit Beschr | Improved cooled gas turbine rotor for high gas-temperatures |
US2931624A (en) * | 1957-05-08 | 1960-04-05 | Orenda Engines Ltd | Gas turbine blade |
DE2357326A1 (de) * | 1973-11-16 | 1975-05-28 | Motoren Turbinen Union | Turbine mit innenkuehlung des kranzes und sollbruchstellen |
FR2381179A1 (fr) * | 1977-02-18 | 1978-09-15 | Rolls Royce | Systeme de refroidissement de turbomachines |
GB2057573A (en) * | 1979-08-30 | 1981-04-01 | Rolls Royce | Turbine rotor assembly |
DE3444586A1 (de) | 1983-12-22 | 1985-07-04 | United Technologies Corp., Hartford, Conn. | Laufradanordnung in einer gasturbine |
DE2947521A1 (de) | 1978-11-27 | 1986-06-26 | Snecma | Turbinenscheibe mit kanaelen zum durchtritt eines kuehlfluids |
EP0353447A1 (de) * | 1988-07-29 | 1990-02-07 | Westinghouse Electric Corporation | Schlitze für den axialen Einschub von Turbinenschaufeln in eine Rotorscheibe |
Family Cites Families (4)
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US4260336A (en) * | 1978-12-21 | 1981-04-07 | United Technologies Corporation | Coolant flow control apparatus for rotating heat exchangers with supercritical fluids |
US5201849A (en) * | 1990-12-10 | 1993-04-13 | General Electric Company | Turbine rotor seal body |
GB2251897B (en) * | 1991-01-15 | 1994-11-30 | Rolls Royce Plc | A rotor |
US5339619A (en) * | 1992-08-31 | 1994-08-23 | United Technologies Corporation | Active cooling of turbine rotor assembly |
-
1997
- 1997-02-13 DE DE19705441A patent/DE19705441A1/de not_active Withdrawn
-
1998
- 1998-01-22 DE DE59800172T patent/DE59800172D1/de not_active Expired - Fee Related
- 1998-01-22 EP EP98101045A patent/EP0859127B1/de not_active Expired - Lifetime
- 1998-02-06 US US09/020,127 patent/US5957660A/en not_active Expired - Fee Related
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE573481C (de) * | 1930-03-23 | 1933-04-01 | Heinrich Ziegler | Gasturbine mit Hohlschaufeln |
US2447292A (en) * | 1943-10-12 | 1948-08-17 | Joseph E Van Acker | Gas-actuated turbine-driven compressor |
GB765225A (en) * | 1954-02-18 | 1957-01-09 | Parsons & Marine Eng Turbine | Improvements in and relating to the cooling of gas turbine blades and rotors |
GB801689A (en) * | 1954-09-10 | 1958-09-17 | Henschel & Sohn Ges Mit Beschr | Improved cooled gas turbine rotor for high gas-temperatures |
US2931624A (en) * | 1957-05-08 | 1960-04-05 | Orenda Engines Ltd | Gas turbine blade |
DE2357326A1 (de) * | 1973-11-16 | 1975-05-28 | Motoren Turbinen Union | Turbine mit innenkuehlung des kranzes und sollbruchstellen |
FR2381179A1 (fr) * | 1977-02-18 | 1978-09-15 | Rolls Royce | Systeme de refroidissement de turbomachines |
DE2947521A1 (de) | 1978-11-27 | 1986-06-26 | Snecma | Turbinenscheibe mit kanaelen zum durchtritt eines kuehlfluids |
GB2057573A (en) * | 1979-08-30 | 1981-04-01 | Rolls Royce | Turbine rotor assembly |
DE3444586A1 (de) | 1983-12-22 | 1985-07-04 | United Technologies Corp., Hartford, Conn. | Laufradanordnung in einer gasturbine |
EP0353447A1 (de) * | 1988-07-29 | 1990-02-07 | Westinghouse Electric Corporation | Schlitze für den axialen Einschub von Turbinenschaufeln in eine Rotorscheibe |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1705339A2 (de) * | 2005-03-23 | 2006-09-27 | ALSTOM Technology Ltd | Rotorwelle, insbesondere für eine Gasturbine |
US7329086B2 (en) | 2005-03-23 | 2008-02-12 | Alstom Technology Ltd | Rotor shaft, in particular for a gas turbine |
EP1705339A3 (de) * | 2005-03-23 | 2013-11-06 | Alstom Technology Ltd | Rotorwelle, insbesondere für eine Gasturbine |
FR2981132A1 (fr) * | 2011-10-10 | 2013-04-12 | Snecma | Ensemble pour turbomachine a refroidissement de disque |
WO2013054043A1 (fr) * | 2011-10-10 | 2013-04-18 | Snecma | Refroidissement de la queue d ' aronde retenant une aube de turbomachine |
US9631495B2 (en) | 2011-10-10 | 2017-04-25 | Snecma | Cooling for the retaining dovetail of a turbomachine blade |
Also Published As
Publication number | Publication date |
---|---|
DE19705441A1 (de) | 1998-08-20 |
DE59800172D1 (de) | 2000-07-20 |
US5957660A (en) | 1999-09-28 |
EP0859127B1 (de) | 2000-06-14 |
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