EP0947669A2 - Traversée de conduite à travers deux ou plusieurs parois du compresseur axial d'une turbine à gaz - Google Patents

Traversée de conduite à travers deux ou plusieurs parois du compresseur axial d'une turbine à gaz Download PDF

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Publication number
EP0947669A2
EP0947669A2 EP99101373A EP99101373A EP0947669A2 EP 0947669 A2 EP0947669 A2 EP 0947669A2 EP 99101373 A EP99101373 A EP 99101373A EP 99101373 A EP99101373 A EP 99101373A EP 0947669 A2 EP0947669 A2 EP 0947669A2
Authority
EP
European Patent Office
Prior art keywords
guide vane
vane carrier
pipeline
gas turbine
housing
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.)
Granted
Application number
EP99101373A
Other languages
German (de)
English (en)
Other versions
EP0947669A3 (fr
EP0947669B1 (fr
Inventor
Emil Dipl.-Ing. Aschenbruck
Michael Dipl.-Ing. Blaswich
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.)
MAN Turbo AG
Original Assignee
MAN Turbomaschinen AG GHH Borsig
GHH Borsig Turbomaschinen GmbH
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=7863613&utm_source=***_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0947669(A2) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by MAN Turbomaschinen AG GHH Borsig, GHH Borsig Turbomaschinen GmbH filed Critical MAN Turbomaschinen AG GHH Borsig
Publication of EP0947669A2 publication Critical patent/EP0947669A2/fr
Publication of EP0947669A3 publication Critical patent/EP0947669A3/fr
Application granted granted Critical
Publication of EP0947669B1 publication Critical patent/EP0947669B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/145—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path by means of valves, e.g. for steam turbines
    • 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

Definitions

  • the invention relates to a pipe bushing through an opening of a guide vane carrier housing and an opening in an outer wall of an axial compressor housing a gas turbine.
  • the pipe duct is made by two or several walls led, due to relative movements horizontally and vertically against each other be moved.
  • the sealing of the pipeline takes place through soft material sealing rings at the outlet opening of the guide vane carrier housing.
  • a disadvantage of this conception is that if elasticity is lost due to the increased temperature of the sealing rings deflect and leakage occurs.
  • the object of the invention is a to create temperature resistant sealing that on the one hand is low-wear and on the other hand one unrestricted freedom of movement of the pipe duct guaranteed in the radial and axial directions.
  • the task is solved according to the characteristic features of the main claim.
  • the dependent claims relate to advantageous embodiments of the pipe duct.
  • the device according to the invention compresses Air from the guide vane carrier housing of an axial compressor a gas turbine via a pipeline taken. Since the guide vane carrier is within the Axial compressor housing, the pipeline through the annulus of the axial compressor, which by the Walls of the vane carrier housing and Compressor housing is formed, are performed.
  • the upper part of the Pipe with flange on the bushing or Extraction nozzle of the compressor housing wall firmly clamped and sealed by two seals.
  • the tube At the leadthrough or outlet opening of the guide vane carrier is the tube through a piston ring sealed.
  • the piston ring allows the relative movement of pipe and compressor housing opposite the guide vane carrier in the vertical direction.
  • the piston ring is passed through on the guide vane carrier wall led two mounting rings.
  • the mounting rings enable relative movement through their free spaces of pipe and compressor housing opposite the guide vane carrier in the horizontal direction.
  • the device according to the invention can be used in all Use cases where one pipe has multiple Walls that are exposed to relative movements, sealed penetrates.
  • the device is also characterized by the Metallic design temperature resistant, there are no wearing parts required. As part of the given freedom is an unrestricted Freedom of movement in radial and axial directions possible. Assembly of the device is very simple. There is a risk of excitation from flow forces locked out.
  • the invention is based on a schematic Embodiment explained in more detail.
  • Fig. 1 shows a longitudinal section through a Axial compressor of a gas turbine with on the shaft (19) arranged blades (21) and in the guide vane carrier (23) attached guide vanes (22) and one arranged below the diffuser (20) on the shaft (19) Impeller (18).
  • Air is transferred from the guide vane carrier (1) via a Pipeline (2) removed. Because the guide vane carrier (1) inside the compressor housing (3) the pipeline (2) must pass through the annulus (4) through the walls of the housings (1) and (3) is formed.
  • the upper tube part (2) has a flange (14) on the passage (6) of the outer housing wall (3) through the extraction nozzle (15) and by means of fastening elements (16) firmly clamped and by two Seals (7) sealed.
  • the piston ring (8) is on the guide vane carrier wall (1) through two mounting rings (9) and (10).
  • the mounting rings (9, 10) allow by their Free spaces or inner and outer dimensions (11, 12, 13) the relative movement of tube (2) and housing (3) opposite the guide vane carrier (1) in horizontal Direction.
  • the device according to the invention can also be Use cases where one pipe (2) has several Walls that are exposed to relative movements, sealed penetrates.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99101373A 1998-04-04 1999-01-26 Traversée de conduite à travers deux ou plusieurs parois du compresseur axial d'une turbine à gaz Expired - Lifetime EP0947669B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19815168 1998-04-04
DE19815168A DE19815168C2 (de) 1998-04-04 1998-04-04 Rohrleitungsdurchführung durch zwei oder mehrere Wandungen eines Axialkompressors einer Gasturbine

Publications (3)

Publication Number Publication Date
EP0947669A2 true EP0947669A2 (fr) 1999-10-06
EP0947669A3 EP0947669A3 (fr) 1999-11-10
EP0947669B1 EP0947669B1 (fr) 2003-05-28

Family

ID=7863613

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99101373A Expired - Lifetime EP0947669B1 (fr) 1998-04-04 1999-01-26 Traversée de conduite à travers deux ou plusieurs parois du compresseur axial d'une turbine à gaz

Country Status (5)

Country Link
US (1) US6216438B1 (fr)
EP (1) EP0947669B1 (fr)
JP (1) JP3760277B2 (fr)
CA (1) CA2266300C (fr)
DE (2) DE19815168C2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1130305A2 (fr) * 2000-03-03 2001-09-05 General Electric Company Réducteur de débit
WO2009143820A3 (fr) * 2008-05-28 2010-01-21 Mtu Aero Engines Gmbh Carter de compresseur de turbine à gaz, compresseur et procédé de fabrication d'un segment de carter de compresseur
WO2010119127A1 (fr) * 2009-04-17 2010-10-21 Siemens Aktiengesellschaft Partie d'un carter, en particulier d'une turbomachine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE0200860D0 (sv) 2002-03-20 2002-03-20 Monica Almqvist Microfluidic cell and method for sample handling
US8360716B2 (en) * 2010-03-23 2013-01-29 United Technologies Corporation Nozzle segment with reduced weight flange
US8695352B2 (en) * 2012-07-12 2014-04-15 Solar Turbines Inc. Baffle assembly for bleed air system of gas turbine engine
GB201610080D0 (en) 2016-06-09 2016-07-27 Rolls Royce Plc Multi-stage compressor with multiple bleed plenums

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH665450A5 (de) * 1983-06-09 1988-05-13 Bbc Brown Boveri & Cie Ventil fuer horizontale dampfzufuehrung an zweigehaeuseturbinen.
DE3905900A1 (de) * 1989-02-25 1990-08-30 Gutehoffnungshuette Man Frischdampfdurchfuehrung fuer dampfturbinen in doppelgehaeusebauart
US5160241A (en) * 1991-09-09 1992-11-03 General Electric Company Multi-port air channeling assembly
DE4136408A1 (de) * 1991-11-05 1993-05-06 Siemens Ag, 8000 Muenchen, De Waermebewegliche anordnung zur abdichtung eines zwischenraumes, insbesondere fuer dampfleitungen bei dampfturbinen

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE757915A (fr) * 1969-10-24 1971-04-01 Gen Electric Construction combinee de carter de compresseur et de collecteurd'air
US3777489A (en) * 1972-06-01 1973-12-11 Gen Electric Combustor casing and concentric air bleed structure
US3967829A (en) * 1973-03-09 1976-07-06 Rogers-Dierks, Inc. Seal ring
US4896499A (en) * 1978-10-26 1990-01-30 Rice Ivan G Compression intercooled gas turbine combined cycle
GB2192229B (en) * 1986-07-04 1990-05-02 Rolls Royce Plc A compressor and air bleed system
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly
DE19545669A1 (de) * 1995-12-07 1997-06-12 Asea Brown Boveri Dampfturbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH665450A5 (de) * 1983-06-09 1988-05-13 Bbc Brown Boveri & Cie Ventil fuer horizontale dampfzufuehrung an zweigehaeuseturbinen.
DE3905900A1 (de) * 1989-02-25 1990-08-30 Gutehoffnungshuette Man Frischdampfdurchfuehrung fuer dampfturbinen in doppelgehaeusebauart
US5160241A (en) * 1991-09-09 1992-11-03 General Electric Company Multi-port air channeling assembly
DE4136408A1 (de) * 1991-11-05 1993-05-06 Siemens Ag, 8000 Muenchen, De Waermebewegliche anordnung zur abdichtung eines zwischenraumes, insbesondere fuer dampfleitungen bei dampfturbinen

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1130305A2 (fr) * 2000-03-03 2001-09-05 General Electric Company Réducteur de débit
EP1130305A3 (fr) * 2000-03-03 2003-11-12 General Electric Company Réducteur de débit
WO2009143820A3 (fr) * 2008-05-28 2010-01-21 Mtu Aero Engines Gmbh Carter de compresseur de turbine à gaz, compresseur et procédé de fabrication d'un segment de carter de compresseur
US8662827B2 (en) 2008-05-28 2014-03-04 MTU Aero Engines AG Housing for a compressor of a gas turbine, compressor, and method for producing a housing segment of a compressor housing
WO2010119127A1 (fr) * 2009-04-17 2010-10-21 Siemens Aktiengesellschaft Partie d'un carter, en particulier d'une turbomachine
EP2243933A1 (fr) * 2009-04-17 2010-10-27 Siemens Aktiengesellschaft Pièce de boîtiers, spécialement d'une turbomachine
US10125633B2 (en) 2009-04-17 2018-11-13 Siemens Aktiengesellschaft Part of a casing, especially of a turbo machine

Also Published As

Publication number Publication date
CA2266300C (fr) 2006-05-30
EP0947669A3 (fr) 1999-11-10
US6216438B1 (en) 2001-04-17
CA2266300A1 (fr) 1999-10-04
DE19815168A1 (de) 1999-10-07
DE59905703D1 (de) 2003-07-03
EP0947669B1 (fr) 2003-05-28
JPH11324613A (ja) 1999-11-26
JP3760277B2 (ja) 2006-03-29
DE19815168C2 (de) 2001-02-22

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