Turbomachine, especially a gas turbine

• US 7,704,042 B2
• Filed: 11/27/2004
• Issued: 04/27/2010
• Est. Priority Date: 12/19/2003
• Status: Active Grant

• Current Assignee: MTU Aero Engines GmbH (MTU)
• Original Assignee: MTU Aero Engines GmbH (MTU)
• Inventors: Feldmann, Manfred, Kislinger, Bernd, Wulf, Joachim, Brueckner, Gerhard
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): WIEHE, NATHANIEL EDWARD
• Application Number:
  US10/582,840
• Publication Number:
  US 20070122270A1
• Time in Patent Office: 1,977 Days
• Field of Search: 415/134, 415/136, 415/139, 415/189, 415/209.1, 415/209.2, 415/209.3, 415/213.1, 415/121.3, 298/892.2, 81/13, 811/244, 811/761.5
• US Class Current: 415/189
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F05B 2260/301 Retaining bolts or nuts
• CPC Class Codes: F05D 2250/41 with one degree of freedom

Abstract

A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). The guide pins (24) extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Claims

1. A turbomachine comprising:

a housing that includes at least a frustoconical sloping housing portion;

a rotor that includes rotor blades rotatably supported in a space within said sloping housing portion so as to be rotatable about an axis of said turbomachine;

a stator ring that includes stator guide vanes arranged in said space within said sloping housing portion axially adjacent to said rotor blades in an axial direction along said axis; and

a spoke-centering arrangement that is arranged and adapted to adjustably support said stator ring relative to said housing and to spoke-center said stator ring about said axis;

wherein;

said spoke-centering arrangement comprises at least three guide pins distributed circumferentially, in a circumferential direction around said axis, about a circumference of said sloping housing portion,

each respective one of said guide pins is secured to said sloping housing portion and respectively extends longitudinally at a slant relative to said axial direction and relative to a radial direction extending radially from said axis, through a respective through-hole in said sloping housing portion so that a respective free end of said respective guide pin protrudes inwardly into said space within said sloping housing portion,

said spoke-centering arrangement further comprises at least three fork-shaped elements distributed circumferentially in said circumferential direction about a circumference of said stator ring,

each respective one of said fork-shaped elements is connected to said stator ring and respectively defines at least a first slot recess between a pair of fork walls of said respective fork-shaped element,

said first slot recess of each respective one of said fork-shaped elements is at least partly open in said radial direction and in said axial direction, and is bounded between said pair of said fork walls in said circumferential direction,

said free end of each said respective one of said guide pins respectively engages into said first slot recess of a respective associated one of said fork-shaped elements while being constrained in said circumferential direction between said pair of said fork walls of said respective associated fork-shaped element and allowing at least a limited relative motion between said respective guide pin and said respective associated fork-shaped element in said radial direction and in said axial direction in which said first slot recess of said respective associated fork-shaped element is at least partly open.

2. The turbomachine according to claim 1, wherein said spoke-centering arrangement comprises exactly seven of said guide pins and correspondingly exactly seven of said fork-shaped elements respectively distributed about said circumference on a radial plane.

3. The turbomachine according to claim 1, wherein said free end of each respective one of said guide pins respectively has a triangular shape as seen in said circumferential direction, with an apex of said triangular shape pointing inwardly into said space within said sloping housing portion along a longitudinal axis of said respective guide pin extending at said slant relative to said axial direction and relative to said radial direction, and wherein said triangular shape lies on a plane extending in said axial direction, and wherein said free end of said respective guide pin is elongated on said plane and parallel to said sloping housing portion.

4. The turbomachine according to claim 1, wherein said spoke-centering arrangement includes nuts that respectively adjustably secure said guide pins on an outer side of said sloping housing portion.

5. The turbomachine according to claim 1, wherein said spoke-centering arrangement further includes a stop arranged on one of said fork-shaped elements so as to bound and limit an axial movability of said one of said fork-shaped elements and said guide vane ring connected thereto, relative to one of said guide pins that engages with said free end thereof into said one of said fork-shaped elements.

6. The turbomachine according to claim 1, wherein said stator ring further includes an outer cover band extending in said circumferential direction and connected to radially outer ends of said stator guide vanes, and wherein said fork-shaped elements are connected to said outer cover band.

7. The turbomachine according to claim 1, further comprising a seal carrier arranged axially adjacent to a radially outer portion of said stator ring.

8. The turbomachine according to claim 7,

wherein said stator ring includes an outer cover band that forms said outer portion of said stator ring, and that extends in said circumferential direction, and that is connected to radially outer ends of said stator guide vanes,

further comprising a seal body carried on a radially inward side of said seal carrier, and

wherein radially outer ends of said rotor blades sealingly cooperate with said seal body.

9. The turbomachine according to claim 7, wherein said seal carrier engages with said guide pins and/or said fork-shaped elements so that said seal carrier is spoke-centered about said axis by said spoke-centering arrangement.

10. The turbomachine according to claim 7, wherein each said fork-shaped element respectively further defines a second slot recess between another pairing of fork walls of said fork-shaped element, said seal carrier includes a projection protruding from a seal carrier member, and said projection is engaged into said second slot recess.

11. The turbomachine according to claim 10, wherein said first slot recess and said second slot recess of said fork-shaped element are positioned circumferentially next to one another with one of said fork walls therebetween in said circumferential direction.

12. The turbomachine according to claim 1, wherein said turbomachine is a turbo-engine.

13. The turbomachine according to claim 1, wherein said turbomachine is a gas turbine.

14. The turbomachine according to claim 1, wherein said guide pins respectively extend longitudinally substantially perpendicularly to said sloping housing portion.

15. The turbomachine according to claim 1, wherein said spoke-centering arrangement includes a first set of said guide pins distributed circumferentially about said circumference of said sloping housing portion on a first plane normal to said axis, a second set of said guide pins distributed circumferentially about said circumference of said sloping housing portion on a second plane normal to said axis and spaced axially from said first plane, a first set of said fork-shaped elements distributed circumferentially about said circumference of said stator ring on said first plane so as to engage respectively with said first set of said guide pins, and a second set of said fork-shaped elements distributed circumferentially about said circumference of said stator ring on said second plane so as to engage respectively with said second set of said guide pins.

16. A combination of the turbomachine according to claim 15 and a mounting tool adapted to carry out an alignment or adjustment of a selected first one of said guide pins of said first set and a selected second one of said guide pins of said second set, wherein said mounting tool comprises a plate-shaped base body having two recesses therein, wherein said plate-shaped base body is positioned on a radially inner side of said sloping housing portion with said respective free ends of said first and second selected guide pins respectively received in said two recesses of said plate-shaped base body so that said first and second selected guide pins are thereby held in an aligned and adjusted position and constrained against turning, and further comprising two nuts respectively tightened onto said first and second selected guide pins on an outer side of said sloping housing portion.

17. The combination according to claim 16, wherein said mounting tool further comprises a handle extending approximately perpendicularly from said plate-shaped base body.

18. The combination according to claim 16, wherein said two recesses of said plate-shaped base body are so configured and arranged such that said respective free ends of said first and second selected guide pins extend longitudinally perpendicularly to a plane along which said plate-shaped base body extends, and such that said plate-shaped base body can be disengaged and removed from said free ends of said first and second selected guide pins tangentially to said plane.