EP1854960B1 - Methode und System zur Drehung eines Turbinenleitschaufelringes - Google Patents
Methode und System zur Drehung eines Turbinenleitschaufelringes Download PDFInfo
- Publication number
- EP1854960B1 EP1854960B1 EP20060252501 EP06252501A EP1854960B1 EP 1854960 B1 EP1854960 B1 EP 1854960B1 EP 20060252501 EP20060252501 EP 20060252501 EP 06252501 A EP06252501 A EP 06252501A EP 1854960 B1 EP1854960 B1 EP 1854960B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- stator
- turbine
- stage
- control signal
- stator ring
- 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.)
- Not-in-force
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/34—Turning or inching gear
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
Definitions
- the present invention relates to methods for distributing the effects of circumferential hot streak conditions in a turbine.
- air is pressurized in a compressor and mixed with fuel and ignited in a combustor for generating combustion gases having high temperatures.
- Energy is extracted from the combustion gases in stages of a turbine.
- the turbine powers the compressor and produces useful work, such as driving a generator to produce power, for example.
- a typical gas turbine directly receives combustion gases from the combustor and includes an initial stage stator and a corresponding initial stage rotor having a plurality of rotor blades or airfoils extending radially outward from a supporting disk. Nozzles disposed around a circumference of each stator stage direct a flow of the combustion gases toward a row of corresponding rotor blades. After the combustion gases pass through the initial stage stator and the initial stage rotor, subsequent stage stators then direct the combustion gases through a corresponding row of rotor blades extending from corresponding subsequent stage rotors. The subsequent stage stators receive lower temperature combustion gases than the initial stage stator and therefore have different cooling requirements. Additionally, individual nozzles within each of the initial and subsequent stator stages often receive combustion gases at different temperatures.
- the nozzles of the turbine are designed for durability with extensive lives measured in hours and/or cycles of operation. Such extended life is difficult to achieve since the nozzles are subject to various differential temperatures during operation, which create thermal stresses on the nozzles. Additionally, nozzles are subjected to oxidation or erosion, which are temperature driven, and coating spallation (when applicable), which is driven by both temperature and thermal stress. Suitable nozzle cooling is required to limit thermal stresses and peak metal temperatures to ensure a useful life. However, temperature distributions and heat transfer coefficients of the combustion gases channeled through each nozzle vary significantly and increase the difficulty of providing suitable nozzle cooling.
- nozzle design engineers typically design all nozzles to be able to withstand worst-case temperatures associated with exposure to hot streak conditions. Additionally, maintenance practices have been developed to inspect and replace nozzles after a certain number of running hours, or to extract nozzles and swap their locations in an effort to equalize accumulated part life consumption among the nozzles.
- US 2003/0002975 relates to a gas turbine wherein the problem of hot streaks is addressed by predetermining an optimal alignment of the stator vanes/nozzles in order to minimize the interaction thereof with the hot streaks.
- the present invention provides a method for distributing effects of a circumferential hot streak condition in a turbine, the method characterised by: communicating a control signal to a rotator; and moving a stator ring including stator nozzles with the rotator in response to the control signal, thereby distributing the circumferential hot streaks among a substantial number of the stator nozzles of the stator ring during operation of the turbine.
- the present invention also provides a turbine comprising: a stator stage including stator nozzles characterised in that the stator stage is rotatable in response to a control signal, thereby to distribute effects of a circumferential hot streak among a substantial number of said nozzles during operation of the turbine.
- the system includes a turbine and a rotator.
- the turbine includes a turbine stator stage rotatable in response to a control signal.
- the rotator is in operable communication with the stator stage and configured to rotate the stator stage in response to the control signal.
- FIG. 1 is a sectional view of a turbine taken along a longitudinal axis of the turbine according to an exemplary embodiment.
- FIG. 2 is a portion of a section cut of a turbine taken along a radial axis showing a perspective view of a turbine stator stage according to an exemplary embodiment.
- the turbine 100 includes a turbine casing 10, a first stage stator 12, a first stage rotor 14, a second stage stator 16, a second stage rotor 18, a third stage stator 20 and a third stage rotor 22.
- Stator and rotor stages 12 through 22 are alternately arranged within the turbine casing 10, such that each of the first, second and third stage stators 12, 16 and 20 is disposed proximate to a corresponding one of the first, second and third stage rotors 14, 18 and 22, respectively.
- the turbine 100 of this exemplary embodiment includes three stages of both stator and rotor, it should be noted that any number of stages may be used in employing the principles discussed hereafter.
- Each one of the first, second and third stage rotors 14, 18 and 22 includes a supporting disk 30 mounted on a shaft (not shown) and rotor airfoils 34.
- the rotor airfoils 34 are mechanically connected to the supporting disk 30, such that the supporting disk 30 may rotate with the shaft in response to a force from combustion gases or another working fluid passing over the rotor airfoils 34. Rotation of the shaft may then be translated as an output to power a compressor (not shown) and produce useful work, for example, in an engine or generator.
- each one of the first, second and third stage stators 12, 16 and 20 includes stator airfoils or nozzles 38 and a stator ring 40.
- the nozzles 38 of each one of the first, second and third stage stators 12, 16 and 20 are mechanically connected to a corresponding stator ring 40.
- the nozzles 38 of the first, second and third stage stators 12, 16 and 20 are disposed proximate to the corresponding rotor airfoils 34 of the first, second and third stage rotors 14, 18 and 22, respectively.
- the nozzles 38 which are substantially static from a perspective of each one of the first, second and third stage rotors 14, 18 and 22, direct a flow of the combustion gases over corresponding rotor airfoils 34.
- each one of the first, second and third stage stators 12, 16 and 20 is non-responsive to the force from combustion gases or another working fluid.
- FIG. 3 is a block diagram illustrating a system for rotating the stator ring 40 according to an exemplary embodiment.
- the stator ring 40 is rotatably mounted within the turbine casing 10.
- a rotator 44 is in operable communication with the stator ring 40.
- the rotator 44 may be in operable communication with more than one stator ring 40.
- the rotator 44 is an apparatus configured to cause a rotation of the stator ring 40 in response to a control signal 46 from a controller 48.
- the stator ring 40 although rotatable, is configured to rotate slowly about a longitudinal axis of the turbine 100 to ensure that the nozzles 38 appear substantially static from the perspective of each one of the first, second and third stage rotors 14, 18 and 22.
- the stator ring 40 rotates at a speed of less than about one revolution per minute (RPM).
- RPM revolution per minute
- the stator ring 40 rotates, for example, in a direction shown by arrow 50, though any direction of rotation is possible.
- the rotator 44 includes any of a number of suitable means to provide a force to rotate the stator ring 40.
- suitable rotator 44 include, but are not limited to, an electric motor, a ratchet assembly, and a combustion engine.
- the rotator 44 may be disposed at the turbine 100 or disposed remote from the turbine 100 and in operable communication with the turbine 100 via, for example, a series of shafts and gears, belts, etc.
- the rotator 44 may derive power from an output of the turbine 100 via a drive assembly having, for example, a series of shafts and reduction gears, etc.
- the rotator 44 provides the force to rotate the stator ring 40 in response to the control signal 46 from the controller 48.
- stator ring 40 may be rotated by a force from a working fluid, for example, a combustion gas, and the rotator 44, responsive to either an active or passive control signal 46, provides a resistive force to slow rotation of the stator ring 40.
- a working fluid for example, a combustion gas
- the rotator 44 responsive to either an active or passive control signal 46, provides a resistive force to slow rotation of the stator ring 40.
- the controller 48 provides the control signal 46 to actuate the rotator 44 and thereby rotate the stator ring 40.
- the controller 48 includes any of many suitable means to provide the control signal 46 to the rotator 44. Examples of a suitable controller 48 include, but are not limited to, a timer, a delay, a logic circuit, a speed regulator and an external actuator that may be controlled by an operator, such as a switch.
- a timer is employed to index or rotate the stator ring 40 at a selected time interval via an electric motor.
- a ratchet assembly indexes the stator ring 40 controlled by a delay between ratchet operations.
- a logic circuit directs an electric motor to index the stator ring 40 in response to selected criteria.
- the stator ring 40 is rotated at a constant differential speed with respect to a speed of a rotor stage via an electric motor controlled by a speed regulator.
- an operator actuates a switch to engage a series of shafts and gears to rotate the stator ring 40.
- Other examples, although not listed herein, are also envisioned.
- the control signal 46 may be communicated to the rotator 44, for example, by an electrical, mechanical, optical or fluid means of transmission.
- the control signal 46 is either a continuously applied signal, such as, for example, an enablement to continuously rotate a ratchet on a delay, or a discretely applied signal, such as, for example, a spring loaded switch having a rotate and a non-rotate position.
- the control signal 46 may be active or passive.
- FIG. 4 is a block diagram illustrating a method for distributing effects of a circumferential hot streak condition in a turbine according to an exemplary embodiment.
- the method includes communicating a control signal to a rotator at block 60 and moving a stator ring with the rotator in response to the control signal at block 62.
- the rotator 44 is capable of operable communication with one or more stator rings 40.
- a number of rotators 44 may be less than or equal to a number of stator rings 40. Since circumferential hot streak conditions are experienced to a greater degree by turbine components disposed closest to an output of the combustor, and cooling requirements are generally decreased as distance from the combustor is increased, it may be desired to rotate the stator ring 40 of only those stator stages that are disposed closest to the output of the combustor, as shown in FIG. 1 .
- controller 48 is configured to apply the control signal 46 to the rotator 44 only during periods that the turbine 100 is off-line. In an alternative exemplary embodiment, the controller 48 is configured to apply the control signal 46 to the rotator 44 during periods that the turbine 100 is on-line.
- turbine casing 12 first stage stator 14 first stage rotor 16 second stage stator 18 second stage rotor 20 third stage stator 22 third stage rotor 30 supporting disk 34 rotor airfoils 38 stator airfoils or nozzles 40 stator ring 44 rotator 46 control signal 48 controller 60 block 62 block 100 turbine
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (10)
- Verfahren zum Verteilen von Auswirkungen eines Zustands in Umfangsrichtung auftretender heißer Schlieren in einer Turbine (100), wobei das Verfahren gekennzeichnet ist durch die Schritte:Übertragen eines Steuersignals (46) an eine Drehvorrichtung (44) (60); undBewegen (62) eines Statorleitschaufeln (38) enthaltenden Statorrings (40) mit der Drehvorrichtung in Antwort auf das Steuersignal (46), um dadurch die in Umfangsrichtung auftretenden heißen Schlieren über eine erhebliche Anzahl von den Statorleitschaufeln (38) des Statorrings (40) während des Betriebs der Turbine (100) zu verteilen.
- Verfahren nach Anspruch 1, wobei der Bewegungsvorgang des Statorrings (40) eines umfasst von:Übertragen einer Drehkraft auf den Statorring (40) über die Drehvorrichtung (44); undWiderstehen einer auf den Statorring (40) wirkenden Drehkraft über die Drehvorrichtung (44), wobei die Drehkraft über ein Arbeitsfluid auf den Statorring (40) übertragen wird.
- Verfahren nach Anspruch 1 oder Anspruch 2, wobei die Bewegung des Statorrings (40) die Drehung des Statorrings (40) um eine Längsachse der Turbine (100) umfasst.
- Verfahren nach einem der vorstehenden Ansprüche, welches ferner den Schritt der Erzeugung des Steuersignals (46) bei einer Steuerung (48) aufweist.
- Verfahren nach Anspruch 4, wobei der Schritt der Erzeugung des Steuersignals (46) bei der Steuerung (48) wenigstens eines aufweist von:Erzeugen eines kontinuierlichen Steuersignals (46); undErzeugen eines diskreten Steuersignals (46).
- Turbine (100), aufweisend:eine Statorstufe (12, 16, 20) mit Statorleitschaufeln (38), dadurch gekennzeichnet, dass die Statorstufe (12, 16, 20) in Antwort auf ein Steuersignal (46) drehbar ist, um dadurch die Auswirkungen einer in Umfangsrichtung auftretenden heißen Schliere über eine erhebliche Anzahl von den Leitschaufeln (38) während des Betriebs der Turbine zu verteilen.
- Turbine nach Anspruch 6, welche ferner eine Rotorstufe (14, 18, 22) aufweist, die unmittelbar an der Statorstufe (12, 16, 20) angeordnet und in Antwort auf einen Strom des Arbeitsfluids drehbar ist, wobei die Statorstufe (12, 16, 20) mit einer gewählten Differenzgeschwindigkeit in Bezug auf eine Drehgeschwindigkeit der Rotorstufe (14, 18, 22) drehbar ist.
- Turbine nach Anspruch 6 oder Anspruch 7, wobei die Statorstufe (12, 16, 20) für eine kontinuierliche Drehung eingerichtet ist.
- Turbine nach Anspruch 8, wobei sich die Statorstufe (12, 16, 20) kontinuierlich mit einer Geschwindigkeit von weniger als einer Umdrehung pro Minute dreht.
- Turbine nach Anspruch 6 oder Anspruch 7, wobei die Statorstufe (12, 16, 20) in diskreten Intervallen drehbar ist.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200660006296 DE602006006296D1 (de) | 2006-05-12 | 2006-05-12 | Methode und System zur Drehung eines Turbinenleitschaufelringes |
EP20060252501 EP1854960B1 (de) | 2006-05-12 | 2006-05-12 | Methode und System zur Drehung eines Turbinenleitschaufelringes |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP20060252501 EP1854960B1 (de) | 2006-05-12 | 2006-05-12 | Methode und System zur Drehung eines Turbinenleitschaufelringes |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1854960A1 EP1854960A1 (de) | 2007-11-14 |
EP1854960B1 true EP1854960B1 (de) | 2009-04-15 |
Family
ID=37232943
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20060252501 Not-in-force EP1854960B1 (de) | 2006-05-12 | 2006-05-12 | Methode und System zur Drehung eines Turbinenleitschaufelringes |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP1854960B1 (de) |
DE (1) | DE602006006296D1 (de) |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5077968A (en) * | 1990-04-06 | 1992-01-07 | United Technologies Corporation | Vaneless contrarotating turbine |
GB2367595A (en) * | 2000-08-08 | 2002-04-10 | Rolls Royce Plc | Actuator mechanism for variable angle vanes having a unison ring directly connected to a vane spindle |
US6554562B2 (en) | 2001-06-15 | 2003-04-29 | Honeywell International, Inc. | Combustor hot streak alignment for gas turbine engine |
-
2006
- 2006-05-12 DE DE200660006296 patent/DE602006006296D1/de active Active
- 2006-05-12 EP EP20060252501 patent/EP1854960B1/de not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
EP1854960A1 (de) | 2007-11-14 |
DE602006006296D1 (de) | 2009-05-28 |
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