EP0799971B1 - Wärmedämmung für einen Turbinenrotor - Google Patents
Wärmedämmung für einen Turbinenrotor Download PDFInfo
- Publication number
- EP0799971B1 EP0799971B1 EP97810142A EP97810142A EP0799971B1 EP 0799971 B1 EP0799971 B1 EP 0799971B1 EP 97810142 A EP97810142 A EP 97810142A EP 97810142 A EP97810142 A EP 97810142A EP 0799971 B1 EP0799971 B1 EP 0799971B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- compressor
- cavities
- turbine
- blades
- 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.)
- Expired - Lifetime
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
Definitions
- the invention relates to the field of power plant technology. It relates to a device for the thermal insulation of compressor rotors thermal turbomachinery, which in particular is applicable for the high pressure compressor sections.
- a liquid-cooled rotor is known from DE 972 310 C. This is used for gas turbines that operate at high Temperatures are operated. This runner is single Rings assembled that support the blades. In order to seal the inside of the rotor outwards, they are Blade rings outside of their clamping by in the axial direction resilient ring body connected together. This bouncy Ring bodies can have a U-shape, for example, in which the legs of the cross section at the open end so are well approximated that the travel is approximately equal to that axial thermal expansion of the rotor. This ensures that no coolant or steam can escape can.
- a turbomachine drum rotor is known from DE-AS 1 068 274, with the radial one open between the rows of blades Ring grooves of small axial width and different Are inserted deep into the drum. This is supposed to deflect favorably influenced by the wave, i.e. a curvature of the Wave can be avoided.
- the invention tries to avoid all of these disadvantages. It is based on the task of a device for thermal insulation of the compressor rotor of a thermal machine create which is easy to carry out and which one adequate protection of the rotor against excessive heat is made possible without the use of heat accumulation segments.
- this is the case with one with several rows Blades equipped compressor rotor of thermal turbo machines, which is around an axis in one of one hot Medium through which the flow channel rotates, being in the rotor several circumferential cavities are provided near the surface are, which each have a separation gap with the flow channel are connected and which each between the Blade rows are arranged, achieved by each of the Cavities have a circular cross-sectional area and that the axial extent of said cavities is approximately as large as the axial distance between two neighboring ones Cavities.
- the advantage of the invention is that with very simple Average thermal insulation can be achieved. To have to no additional expensive heat accumulation segments used become. It can save the time for assembling these elements become.
- the flow channel is opposite previously known prior art more space available, so that the machine can work more effectively.
- the separation gap which connects the heat-insulating, cavity arranged near the surface of the rotor with the surface of the rotor and thus the flow channel produces, an expansion of the rotor surface is easy possible. Due to the circular cross-sectional area of the cavities their notch effect is minimized.
- Fig. 1 shows schematically in a partial longitudinal section a gas turbine system. It essentially consists of one a common shaft 1 arranged compressor 2 and one Turbine 3, wherein between the compressor 2 and the turbine 3 a combustion chamber 4 is provided.
- the combustion chamber 4 is here an annular combustion chamber. Only the last of compressor 2 Rows of the blades 6 arranged in the rotor 5 and in the Blade carrier 7 shown guide vanes 8 shown, while from turbine 3 only the first rows in the rotor 5 arranged turbine blades 9 and those in the turbine blade carrier 10 suspended turbine guide vanes 11 shown are.
- the inlet parts of the compressor 3, the Exhaust casing and the chimney of the turbine are not in Fig. 1 shown.
- Adequate thermal insulation is intended with the present invention of the rotor 5 of the compressor part, in particular the High pressure compressor sections can be achieved. In this area the temperature stress of the rotor 5 is not so extremely high as in the turbine area.
- FIG. 2 shows an embodiment variant of the invention.
- the Cavities 13 are arranged, between each of which here Blade row, not shown, is arranged.
- the Cavities 13 each have a circular cross-sectional area on and are each with a separation gap 14 with connected to the flow channel 15.
- the separation gap 14 allows an expansion of the surface when the compressor is loaded 2 with the hot compressed air and guaranteed thus the compressor 2 runs correctly.
- the axial extension d of the cavity 13 compared to the axial Distance s between two adjacent cavities 13 relative be large, because otherwise there would be insufficient thermal insulation is guaranteed.
- the axial extent d the cavity 13 should not be chosen too large, because otherwise Strength problems would occur in the rotor and moreover there is not enough space to dig the blades would be present.
- the axial extent d of each circumferential cavity 13 is therefore advantageous about as large as the distance s between two neighboring ones Cavities 13.
- This web between the cavities 13 has compared to the Surface a reduced cross-section for braking the heat flow.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Fig. 1
- einen Teillängsschnitt einer Gasturbinenanlage;
- Fig. 2
- einen Teillängsschnitt des Verdichterrotors in einer Ausführungsvariante der Erfindung.
- 1
- Welle
- 2
- Verdichter
- 3
- Turbine
- 4
- Brennkammer
- 5
- Rotor
- 6
- Laufschaufeln von Pos. 2
- 7
- Verdichterschaufelträger
- 8
- Leitschaufeln von Pos. 2
- 9
- Laufschaufeln von Pos. 3
- 10
- Turbinenschaufelträger
- 11
- Leitschaufeln von Pos. 3
- 12
- Rotorachse
- 13
- umlaufender Hohlraum
- 14
- Trennungsspalt
- 15
- Strömungskanal
- d
- axiale Ausdehnung von Pos. 13
- s
- axialer Abstand zwischen benachbarten Pos. 13
Claims (1)
- Vorrichtung zur Wärmedämmung von einem mit mehreren Reihen Laufschaufeln (6) bestückten Verdichterrotor (5) einer thermischen Turbomaschine, insbesondere eines Hochdruckverdichters, welcher um eine Achse (12) in einem von einem heissen Medium durchströmten Strömungskanal (15) rotiert, wobei im Rotor (5) in Oberflächennähe mehrere umlaufende Hohlräume (13) vorgesehen sind, welche jeweils über einen Trennungsspalt (14) mit dem Strömungskanal (15) verbunden sind und welche jeweils zwischen den Laufschaufelreihen (6) angeordnet sind, dadurch gekennzeichnet, dass jeder der Hohlräume (13) eine kreisförmige Querschnittsfläche aufweist, und dass die axiale Ausdehnung (d) jedes Hohlraumes (13) etwa so gross ist wie der axiale Abstand (s) zwischen zwei benachbarten Hohlräumen (13).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19613472 | 1996-04-04 | ||
DE19613472A DE19613472A1 (de) | 1996-04-04 | 1996-04-04 | Vorrichtung zur Wärmedämmung |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0799971A2 EP0799971A2 (de) | 1997-10-08 |
EP0799971A3 EP0799971A3 (de) | 1999-07-07 |
EP0799971B1 true EP0799971B1 (de) | 2002-11-13 |
Family
ID=7790448
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97810142A Expired - Lifetime EP0799971B1 (de) | 1996-04-04 | 1997-03-13 | Wärmedämmung für einen Turbinenrotor |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0799971B1 (de) |
DE (2) | DE19613472A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2551453A1 (de) | 2011-07-26 | 2013-01-30 | Alstom Technology Ltd | Kühlvorrichtung eines Gasturbinenkompressors |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004007327A1 (de) | 2004-02-14 | 2005-09-15 | Alstom Technology Ltd | Rotor |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1068274B (de) * | 1959-11-05 | Gut WöMried Post Rottendorf bei Würzburg Dr.-Ing. Karl Roder | Turbomäschinen-Trommelläufer | |
DE595668C (de) * | 1934-04-16 | Bbc Brown Boveri & Cie | Einrichtung zur Sicherung der Verbindung ineinandergeschobener und gepresster oder geschrumpfter Teile von Laeufern | |
DE1075380B (de) * | 1952-05-22 | 1960-02-11 | Siemens-Schuckertwcrkc Aktiengesellschaft, Berlin und Erlangen | Flüssigkeitsgekühlter, aus Scheiben und Ringen aufgebauter Läufer für Gasturbinen |
US2848193A (en) * | 1953-04-08 | 1958-08-19 | Gen Electric | Air cooled turbomachine blading |
US2858103A (en) * | 1956-03-26 | 1958-10-28 | Westinghouse Electric Corp | Gas turbine apparatus |
DE4324034A1 (de) * | 1993-07-17 | 1995-01-19 | Abb Management Ag | Gasturbine mit gekühltem Rotor |
-
1996
- 1996-04-04 DE DE19613472A patent/DE19613472A1/de not_active Withdrawn
-
1997
- 1997-03-13 EP EP97810142A patent/EP0799971B1/de not_active Expired - Lifetime
- 1997-03-13 DE DE59708687T patent/DE59708687D1/de not_active Expired - Fee Related
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2551453A1 (de) | 2011-07-26 | 2013-01-30 | Alstom Technology Ltd | Kühlvorrichtung eines Gasturbinenkompressors |
DE102012014646A1 (de) | 2011-07-26 | 2013-01-31 | Alstom Technology Ltd. | Kompressorrotor |
US9382802B2 (en) | 2011-07-26 | 2016-07-05 | General Electric Technology Gmbh | Compressor rotor |
Also Published As
Publication number | Publication date |
---|---|
DE59708687D1 (de) | 2002-12-19 |
EP0799971A3 (de) | 1999-07-07 |
EP0799971A2 (de) | 1997-10-08 |
DE19613472A1 (de) | 1997-10-09 |
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