EP2276912B1 - Rotationsmaschine - Google Patents

Rotationsmaschine Download PDF

Info

Publication number
EP2276912B1
EP2276912B1 EP09728480.6A EP09728480A EP2276912B1 EP 2276912 B1 EP2276912 B1 EP 2276912B1 EP 09728480 A EP09728480 A EP 09728480A EP 2276912 B1 EP2276912 B1 EP 2276912B1
Authority
EP
European Patent Office
Prior art keywords
casing
coupling flange
blade ring
turbine
working fluid
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.)
Active
Application number
EP09728480.6A
Other languages
English (en)
French (fr)
Other versions
EP2276912A2 (de
Inventor
Shoki Yamashita
Toshihiro Inoue
Takaaki Matsuo
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.)
Mitsubishi Heavy Industries Ltd
Pebble Bed Modular Reactor Pty Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Pebble Bed Modular Reactor Pty Ltd
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 Mitsubishi Heavy Industries Ltd, Pebble Bed Modular Reactor Pty Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP2276912A2 publication Critical patent/EP2276912A2/de
Application granted granted Critical
Publication of EP2276912B1 publication Critical patent/EP2276912B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to a rotary machine used for a steam turbine, a gas turbine, or the like.
  • a casing used for a steam turbine or a gas turbine is divided into two, i.e., an upper casing and a lower casing in which a rotor shaft is incorporated, and these casings are coupled to each other on a horizontal surface using a bolt (see Patent Japanese Unexamined Utility Model Application, Publication No. S60-195908 , for example).
  • the casing is integrally formed as one piece, a rotor shaft portion is inserted from one end opening of the casing, and the end opening is hermetically closed by fastening a screw ring which is engaged with a screw portion provided on an inner periphery of the casing (see Patent Japanese Unexamined Patent Application, Publication No. S59-213907 , for example).
  • It is an object of the casing structure described above is to secure rigidity of the entire apparatus with respect to working fluid having high temperature and high pressure, and to prevent leak of the working fluid.
  • the upper casing and the lower casing are provided on entire peripheries of the horizontal surfaces thereof with joining flanges, which project from the entire periphery of the horizontal surface of the casing and thus there is a problem that the joined casing itself is increased in size.
  • the joining surface extends over the entire periphery of the horizontal surface of the casing, and thus there is a problem that a range is increased from which the working fluid leaks.
  • a penetrating portion of the rotor shaft is located on the joining surface of the casing, there is a problem that the working fluid leaks easier.
  • the range from which the working fluid leaks can be reduced as compared with a case where the casing is provided on the entire periphery with the joining flanges.
  • the above structure in which the casing is hermetically closed can be employed only to a relatively small turbine, and such a structure must be replaced with a structure provided with flanges in a large turbine. In this case, there are problems that the flange and the joining bolt project in the axial direction, the entire length of the casing is increased, and the entire rotary machine is increased in size.
  • a pressure vessel which further covers the casing is provided, a clean fluid which is not contaminated by the certain material is charged under higher pressure than the working fluid in a space between the pressure vessel and the casing, thereby preventing the fluid in the casing from leaking outside (see Fig. 5 ).
  • Fig. 5 shows a configuration in which a casing 101 of the turbine body described above is accommodated in a pressure vessel (outer casing) 200. Constituent parts of the turbine are accommodated in the casing 101 (not shown).
  • a rotor shaft 4 penetrates the casing 101 and the pressure vessel 200.
  • a clean fluid which has pressure higher than the working fluid in the turbine and which is not contaminated by a certain material is charged in a space 201 between the casing 101 and the pressure vessel 200 so as to prevent the fluid in the casing 101 from leaking outside.
  • the pressure vessel 200 is also increased in size.
  • a blade ring which holds turbine stator blades is mainly supported at the end opening.
  • the blade ring is supported in a cantilever manner.
  • an overhang of the blade ring is made longer and thus, there are problems that a center is not sufficiently be held, and influence of a difference in thermal extension in the axial direction between a rotating portion and a stationary portion is increased.
  • GB 2 024 958 A describes a rotor for a turbomachine having a turbine casing and a combustor casing being connected with each other and interposing a low pressure shroud support and a low pressure nozzle support.
  • the present invention has been accomplished to solve the above problems, and it is an object of the present invention to provide a rotary machine according to claim 1 which can be reduced in size and which can enhance reliability and performance
  • the present invention provides the following means.
  • a casing structure of a turbine according to the present invention includes the features of claim 1.
  • the casing is divided into two in the axial direction, for example on a division surface intersecting with the rotor shaft, and the casing can be reduced in size as compared with a case where the casing is divided into two on the horizontal surface, e.g., on a division surface extending along the rotor shaft.
  • coupling flanges used for fastening the divided casings to each other project outward from the entire periphery of the casing.
  • a cross sectional area of a casing divided into two on vertical surface perpendicular to the rotor shaft becomes smaller than a horizontal cross section of a casing divided into two on the horizontal surface. Therefore, in the casing which is divided into two (first casing and second casing) in the axial direction, the projecting range of the coupling flanges can be made smaller as compared with the casing divided into two on the horizontal surface. In this configuration, the casing can be reduced in size.
  • the third coupling flange which extends from the blade ring in a direction intersecting with the axial direction, more preferably, in a substantially vertical direction, is sandwiched between the first coupling flange of the first casing and the second coupling flange of the second casing which are divided in the axial direction, in assembling the first casing, the second casing and the blade ring.
  • overhang of the blade ring can be reduced.
  • the overhang of the blade ring can be reduced as compared with the pot-like structure described in Japanese Unexamined Patent Application, Publication No. S59-213907 .
  • holding precision of the center of the blade ring with respect to the rotor shaft is enhanced.
  • thermal extension of the blade ring in the axial direction can equally be distributed.
  • connection member disposed between the blade ring and the casing projects from the high-pressure side toward the low-pressure side of the working fluid.
  • the joining member is a conical member which is disposed between the blade ring and the third coupling flange, and which inclines from the high-pressure side to the low-pressure side of the working fluid flowing between the rotor blade and the stator blade radially outward around the rotor shaft.
  • connection member functions as an end plate of the pressure vessel, strength of the connection member is enhanced.
  • the casing is divided into two in the axial direction.
  • leakage of the working fluid to outside the casing and inflow of another fluid into the casing are reduced as compared with a case where the casing is divided into two on the horizontal surface. That is, there is no joining surface of the flange in the penetrating portion of the rotor shaft, leakage of the working fluid to outside the casing and inflow of another fluid into the casing are reduced.
  • an outer peripheral surface of the third coupling flange sandwiched between the first and second coupling flanges of the first and second casings divided in the axial direction may be enclosed between the first and second coupling flanges.
  • the first coupling flange and the second coupling flange may be directly joined to each other radially outside around the rotor shaft, and the first coupling flange and the second coupling flange may be joined radially inside with the third coupling flange sandwiched therebetween.
  • a pressure vessel accommodating the casing therein is provided outside the casing, and a fluid with a pressure higher than the working fluid flowing between the rotor blades and the stator blades is filled in a space between the casing and the pressure vessel.
  • the working fluid is prevented from flowing into the space between the casing and the pressure vessel by charging a fluid having pressure higher than that of the working fluid into the space. Therefore, the working fluid is prevented from flowing outside the casing.
  • the casing is divided into two in the axial direction, there are effects that the casing and the pressure vessel (outer casing) enclosing the casing therein can be reduced in size, leakage of the working fluid to outside the casing and inflow of another fluid into the casing are reduced, and reliability and performance of the rotary machine are enhanced.
  • a casing structure of a gas turbine and the gas turbine having such a casing structure according to an embodiment of the present invention will be described with reference to Figs. 1 to 5 .
  • Fig. 1 is a schematic diagram for describing an entire configuration of the gas turbine according to a first example of the present invention.
  • a gas turbine (rotary machine) 100 includes a casing 101 constituting an outer shape of the gas turbine 100, a blade ring 3 which holds turbine stator blades 10 on an inner periphery thereof, a rotor shaft 4 in which turbine rotor blades 11 are embedded, an inlet scroll portion 5 which supplies a working fluid to a first stage of the turbine stator blades 10, and a discharge scroll portion 6 into which the working fluid discharged from a last stage of the turbine rotor blades 11 flows.
  • the working fluid is accelerated by the turbine stator blades 10, the turbine rotor blades 11 are blown with the accelerated working fluid, and thermal energy of the working fluid is converted into mechanical rotation energy.
  • the rotor shaft 4 is rotated and power is thus taken out.
  • the casing 101 constitutes the outer shape of the gas turbine 100.
  • the blade ring 3, the rotor shaft 4, the inlet scroll portion 5 and the discharge scroll portion 6 are accommodated in the casing 101.
  • the casing 101 is divided into two, namely a high-pressure casing 1 (first casing) and a low-pressure casing 2 (second casing), at substantially a central portion in a direction along the rotor shaft 4.
  • the casings 1 and 2 are substantially cylindrical members whose one ends thereof are closed.
  • the casings 1 and 2 are bottomed cylindrical members, or so-called pot-like members.
  • Outer peripheral portions of the open ends of the casings 1 and 2 have flanges 1A and 2A, respectively.
  • the open ends of the casings 1 and 2 butt against each other, the casings 1 and 2 are fastened to each other with a flange 3A of the later-described blade ring 3 interposed between the flanges 1A and 2A.
  • a through hole 7 into which the rotor shaft 4 is inserted is formed in closed ends of the casings 1 and 2.
  • An opening 8 into which a tube is inserted is provided in cylindrical surfaces of the casings 1 and 2. The working fluid flows into or out of the tube.
  • the blade ring 3 surrounds the rotor shaft 4 together with the casings 1 and 2, constitutes the gas turbine 100 and supports the turbine stator blades 10.
  • the blade ring 3 includes a substantially cylindrical member extending in the axial direction around a rotational axis L, the flange 3A disposed on the outermost peripheral portion, and substantially conical connection member 3B which holds the substantially cylindrical blade ring member by the flange 3A, and the flange 3A is sandwiched between the flanges 1A and 2A.
  • the turbine stator blades 10 are held on the inner periphery of the blade ring 3.
  • the flange 3A is located at substantially the center of the axial length of the blade ring 3.
  • the turbine rotor blades 11 are embedded in the rotor shaft 4, and as shown in Fig. 1 , the turbine rotor blade 11 is blown with the working fluid accelerated by the turbine stator blades 10, so that the rotor shaft 4 is rotated and driven around the rotational axis L.
  • the plurality of turbine stator blades 10 and the plurality of turbine rotor blades 11 are alternately provided, but a known configurations may be employed thereto with no special limitation.
  • the working fluid flows through the inlet scroll portion 5 and the discharge scroll portion 6.
  • the inlet scroll portion 5 supplies the working fluid to the first stage of the turbine stator blades 10, and the working fluid discharged from the last stage of the turbine rotor blades 11 flows into the discharge scroll portion 6.
  • the working fluid heated to a high temperature flows into the inlet scroll portion 5 of the gas turbine 100.
  • the working fluid which has flowed into the inlet scroll portion 5 flows into an annular channel 31, and flows into a cylindrical channel 32 at substantially a constant flow rate in the circumferential direction.
  • the working fluid which has flowed into the cylindrical channel 32 is introduced toward the first stage of the turbine stator blades 10.
  • the turbine rotor blades 11 are rotated and driven by the flowing working fluid, and a rotational driving force extracted by the rotor blades 11 is transmitted to the rotor shaft 4.
  • the working fluid from which rotational driving force is extracted by the turbine rotor blades 11 and of which temperature is lowered is discharged from the last stage of the turbine rotor blades 11.
  • the working fluid which was discharged from the last stage of the turbine rotor blades 11 flows into the cylindrical channel 32 of the discharge scroll portion 6 as shown in Fig. 1 , and flows toward the annular channel 31.
  • the working fluid which has flowed into the annular channel 31 is discharged from the discharge scroll portion 6, i.e., from the gas turbine 100, and is again introduced into the high-temperature gas furnace through each system.
  • the casing 101 in a case where the casing 101 is divided into two in the axial direction, the casing 101 can be reduced in size as compared with a casing which is divided into two on a horizontal surface. More specifically, the flanges 1A and 2A used for fastening the divided casings 1 and 2 to each other project outward from the entire periphery of the casing 101.
  • the area of the cross section which is vertical in the axial direction is smaller than that of a horizontal cross section, a range of projections of the flanges can be made smaller in the casing which is axially divided into two as compared with a configuration in which the casing is divided into two on the horizontal surface.
  • Figs. 2A, 2B , 3A, and 3B schematically show the above-described configuration.
  • Figs. 2A and 2B show a casing structure of a gas turbine in the axial two piece-configuration, and are respectively a plan view and a side view as viewed from the axial direction.
  • Hatched portions 1A and 2A indicate connection flanges provided on the casings 1 and 2 which are divided in the axial direction, and the connection flanges project from the casings 1 and 2.
  • the entire length of the casing 101 is defined as L1, and the diameter of the casing 101 is defined as D1.
  • L1 is greater than D1.
  • an outer shape of the pressure vessel is shown with a chain double-dashed line 200, and its length is defined as L2 and its diameter is defined as D2.
  • Figs. 3A and 3B show a casing structure of a gas turbine in which the casing is divided into two on a horizontal surface, and are respectively a plan view and a side view as viewed from the axial direction.
  • Hatched portions 111A and 112A indicate connection flanges provided respectively on a casing 111 located on the upper side (upper casing) and a casing 112 located on the lower side (lower casing) in the casing divided on the horizontal surface, and the connection flanges project radially outward and axially outward from the casing 111 and the casing 112 around the rotational axis L.
  • the entire length of the casing 101 is defined as L1, and a diameter of the casing 101 is defined as D1.
  • L1 and D1 of the case where the casing is axially divided into two are the same.
  • the outer shape of the pressure vessel is shown with chain double-dashed line 210, and its length is defined as L3 and its diameter is defined as D3.
  • the region of the hatched portion of the axial two piece-configuration (configuration of the present embodiment) shown in Figs. 2A and 2B is smaller than that of the horizontal two piece-configuration (conventional configuration) shown in Figs. 3A and 3B . That is, the range of the projections of the flanges is small.
  • the length L2 of the axial two piece-configuration can be reduced relative to the length L3 of the horizontal two piece-configuration by the width of projections of the flanges.
  • the casing 101 can be reduced in size, the material cost and producing cost can be reduced, and the mass of the entire gas turbine 100 can be reduced. Therefore, it becomes easy to move the gas turbine 100 for inspection or other purposes, and maintainability is enhanced.
  • the gas turbine can be also reduced in size, the material cost and producing cost can be reduced, and a gas turbine room can be reduced in size.
  • the length L1 is longer than the diameter D1 as described above, the axial two piece-configuration results in reduction in size of the casing 101.
  • the casings 1 and 2 and the blade ring 3 are assembled by sandwiching the flange 3A of the blade ring between the coupling flanges 1A and 2A of the casings 1 and 2. Then, overhang of the blade ring 3 can be reduced. More specifically, when the blade ring 3 is held at the substantially central portion in the axial direction with respect to the casing, the overhang of the blade ring 3 can be reduced as compared with the pot-like structure. In this configuration, precision of center hold of the blade ring 3 is enhanced with respect to the rotor shaft 4. Further, since the blade ring 3 is supported at substantially the central portion in the axial direction, axial thermal extension of the blade ring 3 can be equally distributed, and reliability of the gas turbine 100 is enhanced.
  • connection member 3B of the blade ring 3 functions as an end plate in the pressure vessel.
  • a region 12 surrounded by the casing 1 and the blade ring 3 is located on the inlet of the working fluid, and a region 13 surrounded by the casing 2 and the blade ring 3 is located on the outlet of the working fluid. Therefore, a pressure in the region 12 is higher than a pressure in the region 13.
  • resistance to pressure of the connection member 3B is enhanced.
  • connection member 3B is a substantially conical member in the present embodiment, the connection member 3B may have a curved surface as long as it functions as an end plate. In a case where strength required to the connection member 3B is relatively small due to a pressure difference between the regions 12 and 13, the connection member 3B may be of a flat-plate, and the shape thereof is not especially limited.
  • an internal pressure load applied by the pressure of the working fluid to the coupling flanges of the divided surface can be equalized and reduced as compared with the casing is divided into two on the horizontal surface.
  • a pressure receiving area A2 of the flange joining portion is substantially calculated by the following equation (2).
  • a 2 L 1 ⁇ D 1
  • A1 is smaller than A2 from the following equation (3).
  • the internal pressure load applied to the flanges is determined by the pressure receiving area.
  • the inner pressure load is lower in the axial two piece-configuration.
  • Fig. 4 is a schematic diagram for describing an entire configuration of a gas turbine according to a second example of the present invention.
  • a basic configuration of the gas turbine of the present example is the same as that of the first example, but a holding structure of the third coupling flange is different from that of the first example.
  • only the holding structure of the third coupling flange will be described with reference to Fig. 4 , and description of other constituent elements will not be repeated.
  • the constituent elements same as those of the first example are designated with the same symbols, and description thereof will not be repeated.
  • the flange 3A is sandwiched between the flanges 1A and 2A of the casings 1 and 2. Therefore, there are provided two flange joining surfaces on the outer periphery of the casing 101.
  • the configuration of the second example since an outer peripheral portion 3C of the flange 3A is incorporated between the flanges 1A and 2A, the flanges 1A and 2A are directly joined to each other on the outer periphery of the casing 101.
  • the number of joining locations is one, and the peripheral length of the joining surface can be reduced to substantially half. Accordingly, leakage of the working fluid to outside the casing and inflow of another fluid into the casing are reduced.
  • the peripheral length of the cross section of the flange joining portion is shorter in the axial two piece-configuration with respect to that of the horizontal two piece-configuration.
  • Figs. 2A, 2B , 3A, and 3B schematically show the above configuration.
  • Figs. 2A and 2B show the casing structure of the gas turbine of the axial two piece-configuration, and are respectively a plan view and a side view as viewed from the axial direction.
  • the hatched portions 1A and 2A indicate the connection flanges provided on the casings 1 and 2 which are divided into two in the axial direction.
  • the length L1 of the casing 101 is longer than the diameter D1.
  • Figs. 3A and 3B show the casing structure of the gas turbine divided into two on the horizontal surface, and are respectively a plan view and a side view as viewed from the axial direction.
  • the hatched portions 111A and 111B indicate the connection flanges provided respectively on the casing 111 and the casing 112 divided on the horizontal surface.
  • a peripheral length L11 of the cross section of the flange joining portion is substantially calculated by the following equation (5).
  • L 11 2 ⁇ L 1 + D 1
  • L10 is smaller than L11 from the following equation (6).
  • the peripheral length of the cross section of the flange joining portion is shorter in the axial two piece-configuration with respect to that in the horizontal two piece-configuration.
  • the present invention is applied to the axial-flow turbine in the above embodiments, the present invention is not limited to the axial-flow turbine, but the present invention can also be applied to other kinds of turbines such as a centrifugal type turbine and a diagonal-flow turbine.
  • the present invention can also be applied to a general rotary machine of a gas turbine of another type in which air is used as a working fluid and combustion energy of fossil fuel is used as a heat source, a steam turbine, a compressor, or a pump, with no special limitations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (3)

  1. Rotationsmaschine, umfassend
    ein erstes Gehäuse (1) und ein zweites Gehäuse (2), die gebildet sind, indem ein im Wesentlichen zylindrisches Gehäuse (101), das im Inneren davon eine Rotorwelle (4) umschließt, in die Rotorschaufeln (11) eingebettet sind, in zwei unterteilt ist, an im Wesentlichen einem Mittelabschnitt bezüglich einer axialen Richtung der Rotorwelle (4);
    einen ersten Kupplungsflansch (1A) und einen zweiten Kupplungsflansch (2A) an Öffnungen in dem ersten Gehäuse (1) bzw. dem zweiten Gehäuse (2);
    ein Durchgangsloch (7), in das die Rotorwelle (4) eingesetzt ist, das in jedem geschlossenen Ende des ersten Gehäuses (1) bzw. des zweiten Gehäuses (2) gebildet ist;
    einen dritten Kupplungsflansch (3A), der von dem Gehäuse umschlossen ist, wobei der dritte Kupplungsflansch (3A) ein im Wesentlichen zylindrisches Schaufelringelement (3) hält und im Wesentlichen in einer mittleren Position der Länge in axialer Richtung angeordnet ist, wobei das Schaufelringelement (3) Statorschaufeln (10) hält und die Rotorwelle (4) umschließt,
    dadurch gekennzeichnet, dass das erste Gehäuse (1), das zweite Gehäuse (2) und der Schaufelring (3), indem der dritte Kupplungsflansch (3A) zwischen dem ersten Kupplungsflansch (1A) und dem zweiten Kupplungsflansch (2A) eingelegt ist, derart zusammengebaut sind, dass das erste Gehäuse ein Hochdruckgehäuse ist und das zweite Gehäuse ein Niederdruckgehäuse ist;
    wobei die Rotorwelle (4) in die Durchgangslöcher (7), die in den geschlossenen Enden des ersten Gehäuses (1) und des zweiten Gehäuses (2) gebildet sind, eingesetzt ist,
    ein Druckbehälter (210), der das Gehäuse (101) darin aufnimmt, außerhalb des Gehäuses vorgesehen ist; und konfiguriert ist, ein Fluid mit einem Druck zu enthalten, der höher ist als das zwischen den Rotorschaufeln (4) und den Statorschaufeln (10) fließende Arbeitsfluid.
  2. Rotationsmaschine nach Anspruch 1, wobei
    der Schaufelring (3) bezüglich des dritten Kupplungsflansches (3A) durch ein im Wesentlichen konisches Anschlusselement (3B) gehalten ist, und
    eine innere Umfangsfläche an der Schaufelkranzseite des Verbindungselements (3B) von einer Hochdruckseite zu einer Niederdruckseite in einem zwischen den Rotorschaufeln (11) und den Statorschaufeln (10) strömenden Arbeitsfluid vorsteht.
  3. Rotationsmaschine nach Anspruch 1 oder 2, wobei ein Außenumfangsabschnitt des dritten Kupplungsflansches (3A) zwischen dem ersten Kupplungsflansch (1A) und dem zweiten Kupplungsflansch (2A) enthalten ist.
EP09728480.6A 2008-03-31 2009-03-27 Rotationsmaschine Active EP2276912B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2008093753 2008-03-31
PCT/JP2009/056929 WO2009123301A2 (en) 2008-03-31 2009-03-27 Rotary machine

Publications (2)

Publication Number Publication Date
EP2276912A2 EP2276912A2 (de) 2011-01-26
EP2276912B1 true EP2276912B1 (de) 2017-10-25

Family

ID=41136028

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09728480.6A Active EP2276912B1 (de) 2008-03-31 2009-03-27 Rotationsmaschine

Country Status (7)

Country Link
US (1) US20100260599A1 (de)
EP (1) EP2276912B1 (de)
JP (1) JP4969688B2 (de)
CN (1) CN101952557A (de)
RU (1) RU2483218C2 (de)
WO (1) WO2009123301A2 (de)
ZA (1) ZA201003458B (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105579686B (zh) 2013-06-28 2018-02-23 埃克森美孚上游研究公司 利用轴向流膨胀机的系统和方法
CN105324554B (zh) 2013-06-28 2017-05-24 三菱重工压缩机有限公司 轴流膨胀机
EP3128134A1 (de) * 2015-08-06 2017-02-08 Siemens Aktiengesellschaft Anordnung für eine dampfturbine und zugehöriges fixierungsverfahren
CN115163225A (zh) * 2022-07-03 2022-10-11 中国船舶重工集团公司第七0三研究所 一种无中分面的筒形汽缸结构

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5832902A (ja) * 1981-08-20 1983-02-26 Toshiba Corp 蒸気タ−ビン
WO2007094306A1 (ja) * 2006-02-14 2007-08-23 Mitsubishi Heavy Industries, Ltd. ケーシングおよび流体機械

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2374122A (en) * 1942-12-05 1945-04-17 Arthur J Nelson Double case pump
US2408637A (en) * 1944-07-31 1946-10-01 Smith Corp A O Double-casing high-pressure pump
US2815645A (en) * 1955-03-01 1957-12-10 Gen Electric Super-critical pressure elastic fluid turbine
SE403393B (sv) * 1976-07-05 1978-08-14 Stal Laval Turbin Ab Gasturbin
US4222708A (en) * 1978-06-26 1980-09-16 General Electric Company Method and apparatus for reducing eccentricity in a turbomachine
SU832089A1 (ru) * 1979-04-16 1981-05-23 Ордена Ленина И Ордена Трудовогокрасного Знамени Производственноеобъединение "Невский Завод" Им. B.И.Ленина Корпус турбомашины
JPS593103A (ja) * 1982-06-29 1984-01-09 Hitachi Zosen Corp タ−ビンにおける可変静翼装置
JPS6216701U (de) * 1985-07-15 1987-01-31
SU1399485A1 (ru) * 1986-06-10 1988-05-30 А. И. Григорьев, К. И. Сбитнев, В. В. Вдовиков и Н. Е. Першин Способ фиксации фланцев вертикального разъема паровой турбины
FR2608715B1 (fr) * 1986-12-19 1989-12-01 Srti Soc Rech Tech Ind Procede de prevention de fuite de liquide, et dispositif muni de moyens de mise en oeuvre de ce procede
US5080557A (en) * 1991-01-14 1992-01-14 General Motors Corporation Turbine blade shroud assembly
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud
RU2175721C2 (ru) * 1996-04-11 2001-11-10 Сименс Акциенгезелльшафт Способ и устройство для компенсации смещения в турбомашине
FR2794816B1 (fr) * 1999-06-10 2001-07-06 Snecma Stator de compresseur a haute pression
ES2267655T3 (es) * 2001-11-22 2007-03-16 Siemens Aktiengesellschaft Metodo de fabricacion de turbinas de vapor.
FR2860041B1 (fr) * 2003-09-22 2005-11-25 Snecma Moteurs Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par tube a double rotule
FR2891300A1 (fr) * 2005-09-23 2007-03-30 Snecma Sa Dispositif de controle de jeu dans une turbine a gaz
US7273348B2 (en) * 2005-09-23 2007-09-25 General Electric Company Method and assembly for aligning a turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5832902A (ja) * 1981-08-20 1983-02-26 Toshiba Corp 蒸気タ−ビン
WO2007094306A1 (ja) * 2006-02-14 2007-08-23 Mitsubishi Heavy Industries, Ltd. ケーシングおよび流体機械

Also Published As

Publication number Publication date
ZA201003458B (en) 2013-02-27
RU2010125558A (ru) 2012-05-10
EP2276912A2 (de) 2011-01-26
US20100260599A1 (en) 2010-10-14
JP4969688B2 (ja) 2012-07-04
RU2483218C2 (ru) 2013-05-27
CN101952557A (zh) 2011-01-19
JP2011506809A (ja) 2011-03-03
WO2009123301A3 (en) 2010-09-16
WO2009123301A2 (en) 2009-10-08

Similar Documents

Publication Publication Date Title
JP6141871B2 (ja) 高温気体膨張装置の入口ケーシング組立体及び方法
US8221062B2 (en) Device and system for reducing secondary air flow in a gas turbine
JP5364609B2 (ja) タービン・カバープレート・システム
US8727719B2 (en) Annular flange for fastening a rotor or stator element in a turbomachine
EP2187019A1 (de) Abgasteilstruktur einer gasturbine und gasturbine
US8651809B2 (en) Apparatus and method for aligning a turbine casing
US8757964B2 (en) Rotary machine scroll structure and rotary machine
EP2596215B1 (de) Dichtungsanordnung zur regelung eines flüssigkeitsflusses
US9828874B2 (en) Annular cover delimiting a turbomachine lubrication chamber
JP2013139810A (ja) 先端シュラウドを一列に並べる装置及び方法
EP2276912B1 (de) Rotationsmaschine
EP3141698A1 (de) Anordnung für eine gasturbine
EP2283218B1 (de) Wärmeisolationsstruktur
EP0353856A1 (de) Turbinen
RU2479725C2 (ru) Ротор для лопаточной машины с осевым потоком
EP3051072B1 (de) Schaufelmodul
EP3246517B1 (de) Befestigungselementöffnungen zur spannungsverteilung
WO2017162365A1 (en) Damping vibrations in a gas turbine
EP3730745A1 (de) Rotierende blattfederdichtung
US7866949B2 (en) Methods and apparatus for fabricating a rotor for a steam turbine
JP6888941B2 (ja) タービンディフューザのためのシステムおよび方法
RU2291306C2 (ru) Турбомашина, представляющая собой турбину или компрессор, и способ ее сборки
JP6956482B2 (ja) タービンディフューザを支持するシステム
WO2022055686A2 (en) Sacrificial plate in membrane slot for an exit ring
RU2505712C1 (ru) Способ производства химического электронасосного агрегата и химический электронасосный агрегат, выполненный этим способом (варианты)

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20100527

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20160118

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170620

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 940165

Country of ref document: AT

Kind code of ref document: T

Effective date: 20171115

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602009049014

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20171025

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 940165

Country of ref document: AT

Kind code of ref document: T

Effective date: 20171025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180125

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180126

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180225

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180125

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602009049014

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20180726

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180331

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171025

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090327

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171025

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FI

Payment date: 20240315

Year of fee payment: 16

Ref country code: DE

Payment date: 20240220

Year of fee payment: 16

Ref country code: GB

Payment date: 20240222

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240223

Year of fee payment: 16

Ref country code: BE

Payment date: 20240229

Year of fee payment: 16