Turbinenrotor für eine Gasturbine

Ein Turbinenrotor (1) für eine Gasturbine mit einem einteiligen oder in einer ersten Ebene geteilten Kompressorgehäuse (11), einem mit dem Kompressorgehäuse (11) verbundenen einteiligen oder in einer von der ersten Ebene verschiedenen zweiten Ebene geteilten Turbinengehäuse (12) umfasst einen aus wenigstens zwei Kompressorscheiben (2.1-2.5) zusammengesetzten Kompressorbereich und einen Turbinenbereich mit wenigstens einer Turbinenscheibe (13.1, 13.2), wobei die Kompressor- und Turbinenscheiben durch eine Zugankeranordnung mit wenigstens einem Zuganker (6) verspannt sind, die einen ersten Befestigungsbereich, einen zweiten Befestigungsbereich zur Verspannung von wenigstens zwei Kompressorscheiben zwischen dem ersten und dem zweiten Befestigungsbereich, und einen dritten Befestigungsbereich zur Verspannung von wenigstens einer Turbinenscheibe aufweist.

Turbomachine

A turbomachine 1 with axially spaced guide vane rings 35, 36, wherein at least two of the guide vane supports 21, 18 are jointly fastened to and centred on the same housing flange 22. Fastening may be realised by connecting elements 17, such as screws, extending through flanges 9, 23 of the guide vane supports 21, 18 and into the housing flange. The flanges have preferably mating surfaces 3, 4, 20, 28 in an axial direction 16. Radial 15 and circumferential (12, fig. 2) adjustment of the first guide vane support 21 may be effected via first centring elements 24 extending through flange 9 and into casing flange 22. An analogous adjustment is possible for the second guide vane support 18 via second centring elements (33, fig. 3) extending through both flanges 9, 23 and into casing flange 22. Both centring elements may have a first, cylindrical section 6 received within cylindrical bores and a second section 37 of cylindrical basic contour with opposite flats (7, fig. 2) received within elongate ...

CONDUIT PASSING PART PENETRATING TWO OR MORE WALLS IN AXIAL FLOW COMPRESSOR OF GAS TURBINE

PROBLEM TO BE SOLVED: To provide sealing wherein consumption is reduced in one side, an operating freedom not having restriction of a pipe passing part in a radial and axial direction is guaranteed in the other side, and durability is provided in a temperature. SOLUTION: A conduit passing part is provided which is penetrated on an outside opening 17 of a guide impeller support housing 1 of a gas turbine and an opening in an outer wall 3 of an axial flow compressor housing. An upper side part of a pipe 2 provided with a flange 14 and a packing 7 is fixedly fastened between an taking-out pipe piece 15 and the outer wall 3. A lower side part of the pipe 2 is sealed by a piston ring 8. The piston ring 8 is guided by two installing rings 9, 10 which is moved to the guide impeller support housing 1 by an installing element 16. By the installing rings 9, 10, the pipe 2 and the housing 3 are relatively operated with respect to the guide impeller support housing 1 in a horizontal direction. COPYRIGHT ...

Rohrleitungsdurchführung durch zwei oder mehrere Wandungen eines Axialkompressors einer Gasturbine

MULTI-COMPONENT BLADED ROTOR FOR A TURBOMACHINE

The invention relates to a multi-component bladed rotor (1) for a turbomachine, especially a gas or steam turbine or an axial-flow compressor. Said rotor comprises at least two disks (2), the facing front sides of said two disks being connectable in a parting plane, in an especially positive, rotationally fixed manner. A groove (10) is formed in the parting plane, for receiving a blade footing (14) of at least one rotor blade.

PIPELINE DUCT THROUGH TWO OR MORE WALLS OF AN AXIAL COMPRESSOR OF A GAS TURBINE

A pipeline duct through a discharge opening (17) of a vane support housing (1) and an opening (6) in an outer wall (3) of a compressor housing of a gas turbine. The upper part of the pipe (2) is firmly clamped with a flange (14) and seals (7) between the bleeder connection (15) and the outer wall (3) by means of fastening elements (16). The lower part of the pipe (2) is sealed by a piston ring (8). The piston ring (8) is guided by two fastening rings (9, 10), which are mounted in the vane support housing (1) by fastening elements (16). The fastening rings (9, 10) make possible a free movement of the pipe (2) and the housing (3) in relation to the vane support (1) in the horizontal direction due to their free spaces (11, 12, 13).

PIPELINE DUCT THROUGH TWO OR MORE WALLS OF AN AXIAL COMPRESSOR OF A GAS TURBINE

A pipeline duct through a discharge opening (17) of a vane support housing { 1) and an opening (6) in an outer wall (3) of a compressor housing of a gas turbine. The upper part of the pipe (2) is firmly clamped with a flange (14) and seals (7 ) between the bleeder connection (15) and the outer wall (3) by means of fastening elements (16). The lower part of the pipe (2) is sealed by a piston ring (8). The piston ri ng (8) is guided by two fastening rings (9, 10), which are mounted in the vane support housing (1) by fastening elements (16). The fastening rings (9, 10) make possible a free movement of the pipe (2) and the housing (3) in relation to the vane support (1) in the horizontal direction due to their free spaces (11, 12, 13).

Mehrteiliger beschaufelter Rotor für eine Strömungsmaschine

Ein mehrteiliger beschaufelter Rotor (1) für eine Strömungsmaschine, insbesondere eine Gas- oder Dampfturbine oder einen Axialverdichter, weist wenigstens zwei Scheiben (2) auf, deren einander zugewandten Stirnseiten in einer Trennebene (7), insbesondere formschlüssig, drehfest miteinander verbindbar sind, wobei in der Trennebene eine Nut (10) zur Aufnahme eines Schaufelfußes (14) wenigstens einer Laufschaufel ausgebildet ist.

TURBINE ROTOR FOR A GAS TURBINE

A turbine rotor (1) for a gas turbine with a one-piece compressor housing (11) or a compressor housing (11) which is divided in a first plane, a one-piece turbine housing (12) connected to the compressor housing (11) or a turbine housing (12) which is divided in a second plane different from the first plane comprises a compressor area comprising at least two compressor disks (2.1 - 2.5) and a turbine area comprising at least one turbine disk (13.1, 13.2). The compressor disks and turbine disks are clamped together by a tie rod arrangement having at least one tie rod (6) which has a first fastening area, a second fastening area for clamping at least two compressor disks between the first fastening area and the second fastening area, and a third fastening area for clamping at least one turbine disk.

Gas turbine, guide blade ring of a gas turbine and method for producing the same

A gas turbine (10) with a compressor (11) formed as axial compressor, wherein the compressor (11) comprises stator side guide blades (30, 30a) and rotor side moving blades (29), with a burner (13) comprising at least one combustion chamber (21); with a turbine (12); with a diffuser (22) arranged seen in flow direction of the compressed air downstream of the compressor (12), which has an inside wall (26) and an outside wall (27); with an intermediate housing (28) following the outside wall (27). An outlet side guide blade ring (32) of stator side, outlet side guide blades (30a) of the compressor (11) comprises an inner shroud (33) and comprises an outer shroud (34), wherein on the outer shroud (34) of the guide blade ring (32) first fastening devices (35) are formed via which the guide blade ring (32) is directly attached to the intermediate housing (28), and wherein on the inner shroud (33) of the guide blade ring (32) second fastening devices (36) are formed, via which the inside wall ...

FLUID MACHINE

【課題】流体機械の運転に悪影響を与える、入熱に基づく該流体機械内の変形を回避するようにシール剛毛と密封面との接触ゾーンが熱的に遮断されている流体機械を提供する。 【解決手段】流体機械であって、一つのステータ、該ステータに対して回転可能に支承されている一つのロータ、及び、半径方向に形成された一つの隙間をステータとロータとの間で流体が流れないよう密封する一つのブラシシールを備えており、前記ブラシシールは一つのブラシホルダ及び複数のシール剛毛を備えており、該複数のシール剛毛はそれぞれ、前記ブラシホルダに取付けられた第１端部及び一つの密封面と接触している第２端部を備えており、該密封面はそれぞれの前記シール剛毛の前記第２端に対して回転移動可能である、流体機械において、前記密封面が、ステータとロータとの間に配置された、前記隙間を半径方向に分割する一つの中間スリーブの周面で構成されていることを特徴とする。 【選択図】図３

MULTI-COMPONENT BLADED ROTOR FOR A TURBOMACHINE

A multipart bladed rotor (1) for a flow machine, particularly a gas turbine or steam turbine or an axial compressor, has at least two disks (2) whose front sides, which face one another, are connected to one another, particularly by positive engagement, in a separating plane (7) so as to be fixed with respect to rotation relative to one another, wherein a groove (10) for receiving a blade root (14) of at least one rotor blade is formed in the separating plane.

SEALING SEGMENT AND SEALING-SEGMENT ARRANGEMENT

A sealing segment is disclosed for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

FLUID FLOW MACHINE

A fluid flow machine has a stator, a rotor which is supported so as to be rotatable relative to the stator, and a brush seal which seals a gap formed between the stator and rotor in a radial direction to prevent the passage of fluid. The brush seal has a brush holder and a plurality of sealing bristles, each of which has a first end that is fastened to the brush holder and a second end that contacts a sealing surface. The sealing surface is rotationally displaceable relative to the second ends of the respective sealing bristles. The fluid flow machine is characterized in that the sealing surface is formed by a circumferential surface of an intermediate sleeve which is arranged between the stator and rotor and which radially divides the gap.

Rohrleitungsdurchführung durch zwei oder mehrere Wandungen eines Axialkompressors einer Gasturbine

Die Erfindung betrifft eine Rohrleitungsdurchführung durch eine Austrittsöffnung (17) eines Leitschaufelträgergehäuses (1) und einer Öffnung (6) in einer Außenwand (3) eines Kompressorgehäuses einer Gasturbine. Das obere Teil des Rohres (2) ist mit Flansch (14) und Dichtungen (7) fest zwischen Entnahmestutzen (15) und der Außenwand (3) mittels Befestigungselementen (16) verspannt. Der untere Teil des Rohres (2) wird durch einen Kolbenring (8) abgedichtet. DOLLAR A Der Kolbenring (8) wird durch zwei Befestigungsringe (9, 10) geführt, die mittels Befestigungselementen (16) in dem Leitschaufelträgergehäuse (1) verlagert sind. DOLLAR A Die Befestigungsringe (9, 10) ermöglichen durch ihre Freiräume (11, 12, 13) eine Relativbewegung von Rohr (2) und Gehäuse (3) gegenüber dem Leitschaufelträger (1) in horizontaler Richtung.

Gasturbine, Leitschaufelkranz einer Gasturbine und Verfahren zum Herstellen desselben

Gasturbine (10) mit einem als Axialverdichter ausgebildeten Verdichter (11), wobei der Verdichter (11) statorseitige Leitschaufeln (30, 30a) und rotorseitige Laufschaufeln (29) aufweist, mit einem mindestens eine Brennkammer (21) aufweisenden Brenner (13); mit einer Turbine (12); mit einem in Strömungsrichtung der verdichteten Luft gesehen stromabwärts des Verdichters (12) angeordneten Diffusor (22), der eine Innenwand (26) und eine Außenwand (27) aufweist; mit einem sich an die Außenwand (27) anschließenden Zwischengehäuse (28). Ein austrittseitiger Leitschaufelkranz (32) statorseitiger, austrittseitiger Leitschaufeln (30a) des Verdichters (11) verfügt über ein Innendeckband (33) und ein Außendeckband (34) verfügt, wobei am Außendeckband (34) des Leitschaufelkranzes (32) erste Befestigungseinrichtungen (35) ausgebildet sind, über die der Leitschaufelkranz (32) unmittelbar an das Zwischengehäuse (28) befestigt ist, und wobei am Innendeckband (33) des Leitschaufelkranzes (32) zweite Befestigungseinrichtungen (36) ausgebildet sind, über die die Innenwand (25) des Diffusors (22) unmittelbar an dem Leitschaufelkranz (32) befestigt ist. A gas turbine (10) having a compressor (11) designed as an axial compressor, the compressor (11) having stator-side vanes (30, 30a) and rotor-side rotor blades (29) with a burner (13) having at least one combustion chamber (21); with a turbine (12); with a downstream of the compressor (12) arranged in the direction of flow of the compressed air arranged diffuser (22) having an inner wall (26) and an outer wall (27); with an intermediate housing (28) adjoining the outer wall (27). An outlet-side guide vane ring (32) of stator-side, outlet-side vanes (30a) of the compressor (11) has an inner shroud (33) and an outer shroud (34), wherein on the outer shroud (34) of the Leitschaufelkranzes (32) first fastening means (35) are, via the vane ring (32) directly to the intermediate housing (28) is attached, and wherein the inner shroud (33) of the ...

Pipeline duct through two or more walls of an axial compressor of a gas turbine

A pipeline duct through a discharge opening (17) of a vane support housing (1) and an opening (6) in an outer wall (3) of a compressor housing of a gas turbine. The upper part of the pipe (2) is firmly clamped with a flange (14) and seals (7) between the bleeder connection (15) and the outer wall (3) by means of fastening elements (16). The lower part of the pipe (2) is sealed by a piston ring (8). The piston ring (8) is guided by two fastening rings (9, 10), which are mounted in the vane support housing (1) by fastening elements (16). The fastening rings (9, 10) make possible a free movement of the pipe (2) and the housing (3) in relation to the vane support housing (1) in the horizontal direction due to their free spaces (11, 12, 13).

Lagerung des Rotors einer Gasturbine

Der Rotor (5) einer einen Verdichterteil (1) und einen Turbinenteil (3) enthaltenen Gasturbine ist in einem axialen Drucklager (19) und in zwei radialen Traglagern (16, 17) gelagert. Das eine Traglager (16) ist im Eintrittsbereich des Verdichterteiles (1) und das andere Traglager (17) ist zusammen mit dem Drucklager (19) im Bereich des Turbinenteiles (3) angeordnet.

Mounting of the rotor of a gas turbine

Turbine rotor for a gas turbine

A turbine rotor (1) for a gas turbine with a one-piece compressor housing (11) or a compressor housing (11) which is divided in a first plane, a one-piece turbine housing (12) connected to the compressor housing (11) or a turbine housing (12) which is divided in a second plane different from the first plane comprises a compressor area which includes at least two compressor disks (2.1-2.5) and a turbine area which includes at least one turbine disk (13.1, 13.2). The compressor disks and turbine disks are clamped together by a tie rod arrangement which includes at least one tie rod (6) which has a first fastening area, a second fastening area for clamping at least two compressor disks between the first fastening area and the second fastening area, and a third fastening area for clamping at least one turbine disk.

Mounting of the rotor of a gas turbine

The rotor ( 5 ) of a gas turbine containing a compressor part ( 1 ) and a turbine part ( 3 ) is mounted in an axial thrust bearing ( 19 ) and in two radial journal bearings ( 16, 17 ). One of the bearings is a journal bearing ( 16 ) arranged in the intake area of the compressor part ( 1 ) and the other journal bearing ( 17 ) together with the thrust bearing ( 19 ) is arranged in the area of the turbine part ( 3 ).

Turbomaschine

Turbomaschine (1), insbesondere Gasturbine, mit einem statorseitigen Gehäuse (2), mit mehreren statorseitigen Leitschaufelträgern (21, 18), die an dem Gehäuse (2) befestigt sind, mit statorseitigen Leischaufeln (5, 19), die unter Ausbildung axial beabstandeter Leitschaufelkränze (35, 36) an den Leitschaufelträgern (21, 18) befestigt sind, und mit einem mehrere rotorseitige Laufschaufeln tragenden Rotor, wobei jeweils mindestens zwei Leitschaufelträger (21, 18) gemeinsam an einem Flansch (22) des Gehäuses (2) befestigt und zentriert sind.

Gasturbine

Gasturbine, mit einem Verdichter, in welchem Luft verdichtbar; mit einem mindestens eine Brennkammer aufweisenden Brenner, welchem die im Verdichter verdichtete Luft zuführbar ist und in welchem in Anwesenheit der verdichteten Luft ein Brennstoff unter Erhitzung der Luft verbrennbar ist; mit einer Turbine, in welcher die erhitze Luft entspannbar ist; wobei die erhitze Luft ausgehend von der jeweiligen Brennkammer des Brenners der Turbine über ein jeweiliges Zwischenstück (24) zuführbar ist, welches mit einem stromabwärtigen Ende (25) an einem Leitschaufelträger (26) der Turbine, befestigt ist; wobei das jeweilige Zwischenstück (24) an dem stromabwärtigen Ende (25) mindestens ein Befestigungselement (27) mit mindestens einer ein Innengewinde aufweisenden Gewindebohrung (28) aufweist; wobei das jeweilige Befestigungselement (27) des jeweiligen Zwischenstücks (24) in eine Ausnehmung (29) des Leitschaufelträgers (26) der Turbine hineinragt; wobei der Leitschaufelträger (26) mindestens eine ...

GAS TURBINE

The present invention relates to a gas turbine comprising: a compressor in which air can be compressed therein; a combustor having at least one combustion chamber; and a turbine in which heated air can be decompressed therein. The heated air can be supplied from each combustion chamber of the combustor to the turbine via each intermediate component connected to a guide vane carrier of the turbine by a downstream end thereof. As a result, each intermediate component is able to simply be removed from the gas turbine in the axial direction. COPYRIGHT KIPO 2017 ...

BEARING APPARATUS OF A ROTOR IN A GAS TURBINE FOR REDUCING LOSS OF FLOW AND IMPROVING EFFICIENCY BY DECREASING A GAP BETWEEN A ROTOR BLADE AND A STATOR WALL

PURPOSE: A bearing apparatus of a rotor for a gas turbine is provided to decrease loss of flow, and to increase efficiency by arranging a thrust bearing in a turbine area instead of a compressor area and minimizing axial expansion of the turbine portion. CONSTITUTION: A gas turbine comprises a compressor part(1), a combustion chamber(2) and a turbine part(3). A rotor(5) is rotated and assembled with the compressor part and the turbine part by disks(6,7), and supported by an axial thrust bearing(19) and two radial journal bearings(16,17). One radial journal bearing is arranged in the compressor part, and the other radial journal bearing is arranged in the turbine part. The thrust bearing is arranged in the turbine part with the journal bearing. The journal bearing is formed of a floating bearing, and the thrust bearing is formed of a pivot pad bearing. Lubricant is supplied to the thrust bearing from the turbine part through an oil guide hole and an oil discharge line. © KIPO 2006 ...

Gas Turbine, Guide Blade Ring of a Gas Turbine and Method for Producing the Same

A gas turbine with a compressor having stator side guide blades and rotor side moving blades, a burner a combustion chamber; with a turbine); with a diffuser arranged downstream of the compressor, which has an inside wall and an outside wall and; an intermediate housing following the outside wall. An outlet side guide blade ring of stator side, outlet side guide blades () of the compressor has an inner shroud and an outer shroud. First fastening devices are formed on the outer shroud () of the guide blade ring via which the guide blade ring is attached to the intermediate housing, second fastening devices are formed, on the inner shroud () of the guide blade ring via which the inside wall of the diffuser is directly attached to the guide blade ring. 1. A gas turbine , comprising: stator side guide blades; and', 'rotor side moving blades;, 'an axial compressor configured to compress air, comprisinga burner comprising at least one combustion chamber, to which air compressed in the axial compressor is fed and in which a fuel can be combusted in with the compressed air, subject to heating the air;a turbine configured to expand the heated air; an inside wall; and', 'an outside wall;, 'a diffuser arranged downstream of the turbine, as seen in a flow direction of the compressed air, the diffuser comprisingan intermediate housing following the outside wall of the diffuser; outlet side guide blades of the compressor;', 'an inner shroud; and', 'an outer shroud;, 'an outlet side guide blade ring of a stator side, comprisesfirst fastening devices formed on the outer shroud of the outlet side guide blade ring of the stator side guide blades via which the guide blade ring is directly attached to the intermediate housing; andsecond fastening devices formed on the inner shroud of the outlet side guide blade ring of the stator side guide blades via which the inside wall of the diffuser is directly attached to the guide blade ring.2. The gas turbine according to claim 1 , wherein the ...

Multi-component bladed rotor for a turbomachine

A multipart bladed rotor (1) for a flow machine, particularly a gas turbine or steam turbine or an axial compressor, has at least two disks (2) whose front sides, which face one another, are connected to one another, particularly by positive engagement, in a separating plane (7) so as to be fixed with respect to rotation relative to one another, wherein a groove (10) for receiving a blade root (14) of at least one rotor blade is formed in the separating plane.

Sealing Segment and Sealing-Segment Arrangement

A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

Turbomachine

A turbomachine includes: a stator-side housing having: a plurality of stator-side guide vane supports fastened to the stator-side housing, stator-side guide vanes fastened to the stator-side guide vane supports, and axially spaced guide vane rings; and a rotor having a plurality of rotor-side moving blades. At least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing.

Sealing segment and sealing-segment arrangement

A sealing segment for sealingly connecting two structural components parts which are movable relative to one another, with two sealing bodies which are connected to one another by a web and which can be arranged in recesses of the structural component parts in an articulated manner, and a sealing segment arrangement with a plurality of sealing segments of this type, and a flow machine with a sealing segment arrangement of this type.

Mounting of the rotor of a gas turbine

The rotor ( 5 ) of a gas turbine containing a compressor part ( 1 ) and a turbine part ( 3 ) is mounted in an axial thrust bearing ( 19 ) and in two radial journal bearings ( 16, 17 ). One of the bearings is a journal bearing ( 16 ) arranged in the intake area of the compressor part ( 1 ) and the other journal bearing ( 17 ) together with the thrust bearing ( 19 ) is arranged in the area of the turbine part ( 3 ).

TURBOMACHINE

A turbomachine includes: a stator-side housing having: a plurality of stator-side guide vane supports fastened to the stator-side housing, stator-side guide vanes fastened to the stator-side guide vane supports, and axially spaced guide vane rings; and a rotor having a plurality of rotor-side moving blades. At least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing. 11. A turbomachine () comprising:{'b': '2', 'claim-text': [{'b': '22', 'a flange (),'}, {'b': 21', '18', '2', '21', '18', '9', '23, 'first and second stator-side guide vane supports (, ) each being fastened to the stator-side housing (), the first and second stator-side guide vane supports (, ) having respective first and second guide vane support flanges (, ),'}, {'b': 5', '19', '21', '18, 'first and second stator-side guide vanes (, ) fastened to the first and second stator-side guide vane supports (, ), respectively, and'}, {'b': 35', '36', '5', '19, 'first and second axially spaced guide vane rings (, ) associated with the first and second stator-side guide vanes (, ), respectively; and'}], 'a stator-side housing (), havinga rotor having a plurality of rotor-side moving blades,{'b': 21', '18', '22', '2, 'wherein at least two of the first and second stator-side guide vane supports (, ) are jointly fastened to and centered on the flange () of the stator-side housing ().'}217211822217923222222. The turbomachine according to claim 1 , further comprising connecting elements () claim 1 , wherein the first and second stator-side guide vane supports ( claim 1 , ) are fastened to the flange () of the stator-side housing () by the connecting elements () extending through the respective first and second guide vane support flanges ( claim 1 , ) claim 1 , which are jointly fastened to and centered on the flange () of the stator-side housing () claim 1 , and into the flange () of the stator-side housing ().3212221649322218222162823209. The turbomachine according to ...

BEARING DEVICE OF ROTOR OF GAS TURBINE

PROBLEM TO BE SOLVED: To provide a bearing device of a rotor of a gas turbine capable of reducing a clearance between parts by reducing the relative elongation of the turbine rotor to a turbine stator. SOLUTION: This device is formed so that the rotor 5 of the gas turbine having a compressor part 1 and a turbine part 3 is pivotally supported on an axial thrust bearing 19 and two radial supporting bearings 16 and 17. One of the supporting bearings 16 is disposed in the inlet area of the compressor part 1, and the other support bearing 17 is disposed in the area of the turbine part 3 together with the thrust bearing 19. COPYRIGHT: (C)2005,JPO&NCIPI ...

Sealing segment and sealing-segment arrangement

Offenbart ist ein Dichtsegment zum dichtenden Verbinden von zwei relativ zueinander bewegbaren benachbarten Bauteilen, mit zwei Dichtkörpern, die über einen Steg miteinander verbunden und in Ausnehmungen der Bauteile gelenkig anordbar sind, sowie eine Dichtsegmentenanordnung mit einer Vielzahl von derartigen Dichtsegmenten und eine Strömungsmaschine mit einer derartigen Dichtsegmentenanordnung.

Fluid Flow Machine

A fluid flow machine has a stator, a rotor which is supported so as to be rotatable relative to the stator, and a brush seal which seals a gap formed between the stator and rotor in a radial direction to prevent the passage of fluid. The brush seal has a brush holder and a plurality of sealing bristles, each of which has a first end that is fastened to the brush holder and a second end that contacts a sealing surface. The sealing surface is rotationally displaceable relative to the second ends of the respective sealing bristles. The sealing surface is formed by a circumferential surface of an intermediate sleeve which is arranged between the stator and rotor and which radially divides the gap.

turbomachine

Turbomaschine (1), insbesondere Gasturbine, mit einem statorseitigen Gehäuse (2), mit mehreren statorseitigen Leitschaufelträgern (21, 18), die an dem Gehäuse (2) befestigt sind, mit statorseitigen Leitschaufeln (5, 19), die unter Ausbildung axial beabstandeter Leitschaufelkränze (35, 36) an den Leitschaufelträgern (21, 18) befestigt sind, und mit einem mehrere rotorseitige Laufschaufeln tragenden Rotor, dadurch gekennzeichnet, dass jeweils mindestens zwei Leitschaufelträger (21, 18) gemeinsam an einem Flansch (22) des Gehäuses (2) befestigt und zentriert sind, und wobei jeder der Leitschaufelträger (21, 18) jeweils mehrere Leitschaufeln (5, 19) unter Ausbildung jeweils eines Leitschaufelkranzes (35, 36) aufnimmt. Turbomachine (1), in particular a gas turbine, with a housing (2) on the stator side, with a plurality of guide vane carriers (21, 18) on the stator side, which are fastened to the housing (2), with guide vanes (5, 19) on the stator side, which form axially spaced Guide vane rings (35, 36) are fastened to the guide vane carriers (21, 18), and with a rotor carrying a plurality of moving blades on the rotor side, characterized in that at least two guide vane carriers (21, 18) are jointly attached to a flange (22) of the housing (2nd ) are fastened and centered, and wherein each of the guide vane carriers (21, 18) accommodates a plurality of guide vanes (5, 19), each forming a guide vane ring (35, 36).

Sealing segment and sealing segment arrangement

Offenbart ist ein Dichtsegment zum dichtenden Verbinden von zwei relativ zueinander bewegbaren benachbarten Bauteilen, mit zwei Dichtkörpern, die über einen Steg miteinander verbunden und in Ausnehmungen der Bauteile gelenkig anordbar sind, sowie eine Dichtsegmentenanordnung mit einer Vielzahl von derartigen Dichtsegmenten und eine Strömungsmaschine mit einer derartigen Dichtsegmentenanordnung. Disclosed is a sealing segment for sealingly connecting two relatively movable adjacent components, with two sealing bodies which are interconnected via a web and articulated in recesses of the components, and a sealing segment arrangement with a plurality of such sealing segments and a turbomachine with such a sealing segment arrangement ,

Gas turbine, guide blade ring of a gas turbine and method of producing the same

A gas turbine (10) with a compressor (11) formed as axial compressor, wherein the compressor (11) comprises stator side guide blades (30, 30a) and rotor side moving blades (29), with a burner (13) comprising at least one combustion chamber (21); with a turbine (12); with a diffuser (22) arranged seen in flow direction of the compressed air downstream of the compressor (12), which has an inside wall (26) and an outside wall (27); with an intermediate housing (28) following the outside wall (27). An outlet side guide blade ring (32) of stator side, outlet side guide blades (30a) of the compressor (11) comprises an inner shroud (33) and comprises an outer shroud (34), wherein on the outer shroud (34) of the guide blade ring (32) first fastening devices (35) are formed via which the guide blade ring (32) is directly attached to the intermediate housing (28), and wherein on the inner shroud (33) of the guide blade ring (32) second fastening devices (36) are formed, via which the inside wall (25) of the diffuser (22) is directly attached to the guide blade ring (32). Fig. 2

ガスタービン

【課題】新規のガスタービンを提供する。【解決手段】中間ピース（２４）は、下流端（２５）に、雌ネジを持つ少なくとも一つのねじ穴（２８）を有する少なくとも一つの固定要素（２７）を有しており；中間ピース（２４）の固定要素（２７）は、タービンのガイドベーン支持部（２６）のリセス（２９）内に突き出しており；ガイドベーン支持部（２６）は、少なくとも一つの無ネジ山貫通溝（３０）を有していて、これは、中間ピース（２４）の方を向いているセクションにおいて軸方向において開いているように形成されており；中間ピース（２４）の固定要素（２７）は、少なくとも一つの無ネジ山貫通穴、及び、保持要素（３１）の貫通穴、ガイドベーン支持部（２６）の貫通溝（３０）、及び固定要素（２７）のネジ穴（２８）を貫いている、少なくとも一つの固定ボルト（３２）を有する、保持要素（３１）を介してガイドベーン支持部（２６）に取付けられている。【選択図】図２

Gasturbine.

Gasturbine, mit einem Verdichter, in welchem Luft verdichtbar ist; mit einem mindestens eine Brennkammer aufweisenden Brenner, welchem die im Verdichter verdichtete Luft zuführbar ist und in welchem in Anwesenheit der verdichteten Luft ein Brennstoff unter Erhitzung der Luft verbrennbar ist; mit einer Turbine, in welcher die erhitzte Luft entspannbar ist; wobei die erhitzte Luft ausgehend von der jeweiligen Brennkammer des Brenners der Turbine über ein jeweiliges Zwischenstück (24) zuführbar ist, welches mit einem stromabwärtigen Ende (25) an einem Leitschaufelträger (26) der Turbine befestigt ist; wobei das jeweilige Zwischenstück (24) an dem stromabwärtigen Ende (25) mindestens ein Befestigungselement (27) mit mindestens einer ein Innengewinde aufweisenden Gewindebohrung (28) aufweist; wobei das jeweilige Befestigungselement (27) des jeweiligen Zwischenstücks (24) in eine Ausnehmung (29) des Leitschaufelträgers (26) der Turbine hineinragt; wobei der Leitschaufelträger (26) mindestens eine gewindelose Durchgangsnut (30) aufweist, die an einem dem jeweiligen Zwischenstück (24) zugewandten Abschnitt axial offen ausgebildet ist; wobei das jeweilige Befestigungselement (27) des jeweiligen Zwischenstücks (24) über ein jeweiliges Halteelement (31) mit mindestens einer gewindelosen Durchgangsbohrung und mit mindestens einer die jeweilige Durchgangsbohrung des Halteelements (31), die jeweilige Durchgangsnut (30) des Leitschaufelträgers (26) und die jeweilige Gewindebohrung (28) des jeweiligen Befestigungselements (27) durchdringenden Befestigungsschraube (32) am Leitschaufelträger (26) montiert ist.

Gasturbine.

Es wird eine Gasturbine (10), mit einem Verdichter (11) vorgeschlagen, in welchem Luft verdichtbar ist und einem mindestens eine Brennkammer (21) aufweisenden Brenner (13), in welchen die im Verdichter (11) verdichtete Luft zuführbar ist und in welchem in Anwesenheit der verdichteten Luft ein Brennstoff unter Erhitzung der Luft verbrennbar ist. In der vorgeschlagenen Turbine (12), ist die erhitze Luft entspannbar, wobei die erhitze Luft ausgehend von der jeweiligen Brennkammer (21) des Brenners der Turbine (12) über ein jeweiliges Zwischenstück (24) zuführbar ist, welches mit einem stromabwärtigen Ende an einem Leitschaufelträger der Turbine, befestigt ist. An dem jeweiligen Zwischenstück (24) an dem stromabwärtigen Ende ist mindestens ein Befestigungselement angebracht, welches mindestens eine ein Innengewinde aufweisende Gewindebohrung aufweist. Das jeweilige Befestigungselement des jeweiligen Zwischenstücks (24) ragt in eine Ausnehmung des Leitschaufelträgers der Turbine hinein. Die vorgeschlagene Gasturbine (10) ermöglicht es, dass die jeweiligen Zwischenstücke (24) mit geringerem Montageaufwand ersetzt werden können.