EP0162340A1 - Apparat zur Regelung der axialen Laufspielkomponente in Radialgasturbinen - Google Patents

Apparat zur Regelung der axialen Laufspielkomponente in Radialgasturbinen Download PDF

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Publication number
EP0162340A1
EP0162340A1 EP85105154A EP85105154A EP0162340A1 EP 0162340 A1 EP0162340 A1 EP 0162340A1 EP 85105154 A EP85105154 A EP 85105154A EP 85105154 A EP85105154 A EP 85105154A EP 0162340 A1 EP0162340 A1 EP 0162340A1
Authority
EP
European Patent Office
Prior art keywords
turbine
shroud
axial
nozzle assembly
assembly
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.)
Ceased
Application number
EP85105154A
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English (en)
French (fr)
Inventor
Ivar Austrem
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.)
Kongsberg Gruppen ASA
Original Assignee
Kongsberg Vapenfabrikk AS
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 Kongsberg Vapenfabrikk AS filed Critical Kongsberg Vapenfabrikk AS
Publication of EP0162340A1 publication Critical patent/EP0162340A1/de
Ceased 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
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations

Definitions

  • the present invention relates to an apparatus for controlling the axial component of the running clearance between a radial-inflow gas turbine and a cooperating turbine shroud.
  • turbine shroud In most types of turbine machinery, turbine blades are ro- tated on a shaft and the radially outward edge of the blades is enveloped by a casing, referred to hereinafter as a turbine shroud.
  • the gap between the edge of the blades and the inner surface of the shroud is known as running clearance.
  • an increase in the running clearance causes a corresponding decrease in turbine efficiency.
  • Increases in running clearance develop primarily in response to the engine growth resulting from the thermal effects of turbine operation.
  • a small, high performance and high ef- ficiency turbine is more sensitive to variations in running clearance than a large, low or medium performance engine.
  • a 1% increase in turbine running clearance can cause a 0.38% reduction in both power output and thermal efficiency.
  • Figure 1A discloses a shroud which is fixedly attached to a turbine nozzle assembly 3 which, in turn is attached to frame 1 by nozzle assembly exten- sion 2.
  • Expansion vectors 1 through 5 in the turbine growth diagram of Figure 1B depict the response to turbine operation by the principal rotating and static parts of turbine machinery.
  • the expansion vectors correspond to materials capable of withstanding excessive turbine temperature and commonly used in turbine construction at the noted positions.
  • The-thermal expansion-induced growth in actual running clearance of the turbine depicted in Figure IA is about 1.2 mm when measured from about room temperature to steady state operation with a turbine inlet temperature of about 1100'C.
  • the apparatus for controlling the axial component of the running clearance between a radial-inflow turbine and the corresponding turbine shroud the turbine of the type being fixed to a shaft and the shaft being rotatably supported at one end by a frame assembly, the shaft and the turbine changing in position in the axial direction relative to the frame with changes in turbine operating temperature
  • the apparatus comprising a shroud mounting assembly including the shroud, a turbine nozzle assembly, the nozzle assembly being connected to the shroud mounting assembly, means for slidably connecting the turbine nozzle assembly to the frame for axial sliding movement therewith, and means for adjusting the axial position of the shroud relative to the frame to compensate for changes in the turbine axial position and for controlling the relative axial displacement of the shroud
  • the adjusting means including axial spacer means fixedly connecting the turbine nozzle assembly to the frame, the spacer means being positioned to be subjected to temperature changes corresponding to the turbine temperature changes
  • Gas turbine 10 also comprises rotor hub 16 and turbine blades 18 mounted on hub 16 for rotation about turbine axis 19.
  • a tie bolt 20 is connected to hub 16 and is enveloped by a rotor coupling 21.
  • gas turbine 10 is of the radial-inflow, axial- outflow type. That is, hot combustion gases are fed through turbine inlet nozzle 12 of nozzle assembly 24 essentially in a radial direction. Thereafter, the hot gases flow into a region 22 swept by rotating blades 18 and are expanded to produce power. The expanded gases leave turbine 10 in an axial direction as indicated by an arrow designated "A". This flow of hot combustion gases creates a substantial rise in temperature throughout turbine 10 and corresponding axial and radial expansion of the components therein.
  • turbine nozzle assembly 24 is positioned axially between frame 11 and shroud 14. The forward portion of nozzle assembly 24 is connected to frame 11.
  • the nozzle assembly includes inlet 12, and nozzle wall members 26 and 28. Walls 26 and 28-form the outer surface of turbine nozzle assembly 24.
  • the gas turbine also includes means for slidably connecting the turbine nozzle assembly to the turbine frame to allow axial sliding movement therewith.
  • slidably connecting means 29 includes an individual cylindrically-shaped axial extension 30 at the base of the wall member 26 that is directed away from inlet nozzle 12.
  • Slidably connecting means 29 further includes a frame support member 31 having flange 32, which is rigidly affixed to frame 11.
  • Axial extension 30 engages flange 32 to allow continuous sliding contact therebetween at a point B, in response to changes in turbine operating temperature.
  • axial extension 30 is shown to be positioned radially inward of flange 32 of frame support member 31 at point B. The relative positions of flange 32 and axial extension 30 may be reversed while not departing from the scope of the invention.
  • the turbine further includes means for controlling the axial position of the turbine nozzle assembly relative to the frame to compensate for changes in the turbine axial position and for controlling the relative axial displacement of the shroud.
  • control- ling means 33 include axial spacer means 34 fixedly connecting turbine nozzle assembly 24, and specifically nozzle wall member 26, to frame 11.
  • Axial spacer means 34 preferably include a plurality of individual struts 36 positioned radially outward of slidably connecting means 29 and spaced discontinuously in the circumferential direction around turbine 10.
  • fourteen struts of about 16cm in length are distributed circumferentially around turbine 10.
  • Struts 36 take the shape of a longitudinal bar having L-shaped facing edges 37 and 38 at opposite ends. Bolts 40, 41 or equivalent means, are used to connect edge 37 with frame 11, and edge 38 with wall member 26, respectively. The radial inward surface of strut 36 is supported at the forward end by frame support member 31 and at the rear end by portion of axial extension 30.
  • struts 36 are continuously subjected to various temperature changes during turbine operation and should be formed from a material having an extremely low coefficient of thermal expansion relative to the coefficient correponding the other turbine components, such as shroud 14 and turbine nozzle assembly 22.
  • struts 36 are composed of a material having a coefficient of thermal expansion of about 5x10 -6 °C or less, which is, characteristic of a material such as NILO 42.
  • the controlling means further includes means for attaching the shroud mounting assembly to the turbine nozzle assembly.
  • the attaching means includes second axial spacer means 48 positioned radially outward of shroud mounting assembly 13. Second spacer means are intended to be sensitive to temperature changes within turbine 10, and provide relative axial movement between shroud 14 and turbine nozzle assembly 24.
  • second spacer means 48 generally consist of an axially extending cone-shaped member 50 surrounding turbine 10 having an axial length of about 10.4cm are used.
  • Cone 50 is typically formed of a material having a low level of thermal expansion with respect to other turbine components such as shroud 14.
  • cone 50 has a coefficient of thermal expansion of about 8x10 6°C -1 or less, as can be obtained with material such as INCO 907.
  • shroud assembly 13 includes shroud 14 in the form of a flared annular member, which is positioned adjacent turbine nozzle assembly 24 and substantially corresponds to an axially outer surface of revolution traced by blades 18. The shroud extends from a point adjacent turbine nozzle assembly 24, to a point beyond turbine blades 18 and essentially parallel to turbine axis 19.
  • shroud assembly 13 includes shroud support member 15 having a form which substantially corresponds to the radially outer surface of shroud 14 and also having a space therebetween to provide a passage for coolant gas flow.
  • a conduit 51 admits coolant gas which flows between shroud 14 and shroud support member 15.
  • Shroud 14 is formed of a material having a high coefficient of thermal expansion relative to other turbine components such as struts 36 and cone 50.
  • Cone 50 is rigidly attached between turbine nozzle assembly 24 and a rear portion of support member 15.
  • Mounting pad 52 with integral flow passages and a clamping ring 54 rigidly attaches the forward end of cone-shaped member 50 to turbine nozzle assembly 24.
  • Upwardly extending flange 56 on shroud support member 15 radially distant from turbine nozzle assembly 24 is rigidly atta- ched to the rear end of cone-shaped member 50 by bolts 58.
  • shroud mounting assembly 13 includes ring 60, which clamps shroud 14 to shroud support 15. Ring 60 seals the forward ends of shroud 14 and shroud support member 15 against the escape of cooling air admitted through conduit 51. Ring 60 further provided sealing contact with the radially inner edge of nozzle assembly 24 to prevent ingestion of combustion gazes into the flow of coolant gas while allowing relative axial movement. Flexible seal 64 is positioned between shroud support 15 and inward base projection 62 of nozzle wall 2 8 and also facilitates relative axial movement of shroud mounting assembly 13.
  • Figure 2B displays a net growth of .2mm in actual turbine clearance at point C for the depicted turbine, measured from room temperature assembly to steady state running temperature.
  • the line of reference characterized by the phantom line between Figures 2A and 2B is established at the only point of zero relative axial movement between the rotating and static turbine elements.
  • the expansion vectors correspond to materials capable of in turbine construction at the noted positions.
  • the noted turbine elements may be formed from materials, such as frame support member 31 - AISI 410, nozzle wall members 26 and 28 - IN 718, and inlet nozzle 12 - X 40.
  • rotor coupling 21 should be formed of material other than stainless steel, such as SS 2240.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Yarns And Mechanical Finishing Of Yarns Or Ropes (AREA)
EP85105154A 1984-05-15 1985-04-26 Apparat zur Regelung der axialen Laufspielkomponente in Radialgasturbinen Ceased EP0162340A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US61047984A 1984-05-15 1984-05-15
US610479 1984-05-15

Publications (1)

Publication Number Publication Date
EP0162340A1 true EP0162340A1 (de) 1985-11-27

Family

ID=24445174

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85105154A Ceased EP0162340A1 (de) 1984-05-15 1985-04-26 Apparat zur Regelung der axialen Laufspielkomponente in Radialgasturbinen

Country Status (2)

Country Link
EP (1) EP0162340A1 (de)
JP (1) JPS611807A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2860041A1 (fr) * 2003-09-22 2005-03-25 Snecma Moteurs Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par tube a double rotule
US9291070B2 (en) 2010-12-03 2016-03-22 Pratt & Whitney Canada Corp. Gas turbine rotor containment

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011056657A2 (en) 2009-10-27 2011-05-12 Harmonix Music Systems, Inc. Gesture-based user interface
US8001792B1 (en) * 2010-04-08 2011-08-23 Opra Technologies B.V. Turbine inlet nozzle guide vane mounting structure for radial gas turbine engine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1889554A (en) * 1930-06-27 1932-11-29 Laval Steam Turbine Co Steam chest construction for steam turbines
US2283176A (en) * 1937-11-29 1942-05-19 Turbo Engineering Corp Elastic fluid mechanism
US2383948A (en) * 1943-01-22 1945-09-04 Gen Electric Gas turbine
US2429936A (en) * 1943-12-18 1947-10-28 Allis Chalmers Mfg Co Turbine mounting
CH268647A (fr) * 1947-12-08 1950-05-31 Armstrong Siddeley Motors Ltd Turbine à combustion interne.
GB842093A (en) * 1956-02-03 1960-07-20 Power Jets Res & Dev Ltd Improvements in or relating to a compressor-gas turbine combination incorporating supporting structure for apparatus subject to temperature variations
DE1220671C2 (de) * 1963-02-15 1967-02-23
US3384345A (en) * 1966-08-15 1968-05-21 United Aircraft Canada Radial turbine shroud construction

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1889554A (en) * 1930-06-27 1932-11-29 Laval Steam Turbine Co Steam chest construction for steam turbines
US2283176A (en) * 1937-11-29 1942-05-19 Turbo Engineering Corp Elastic fluid mechanism
US2383948A (en) * 1943-01-22 1945-09-04 Gen Electric Gas turbine
US2429936A (en) * 1943-12-18 1947-10-28 Allis Chalmers Mfg Co Turbine mounting
CH268647A (fr) * 1947-12-08 1950-05-31 Armstrong Siddeley Motors Ltd Turbine à combustion interne.
GB842093A (en) * 1956-02-03 1960-07-20 Power Jets Res & Dev Ltd Improvements in or relating to a compressor-gas turbine combination incorporating supporting structure for apparatus subject to temperature variations
DE1220671C2 (de) * 1963-02-15 1967-02-23
US3384345A (en) * 1966-08-15 1968-05-21 United Aircraft Canada Radial turbine shroud construction

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2860041A1 (fr) * 2003-09-22 2005-03-25 Snecma Moteurs Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par tube a double rotule
EP1519009A1 (de) * 2003-09-22 2005-03-30 Snecma Moteurs Turbomaschine mit Luftentnahme für die Kabine über ein Kugelgelengrohr
US7409831B2 (en) 2003-09-22 2008-08-12 Snecma Provision of sealing in a jet engine for bleeding air to the cabin using a tube with a double ball joint
US9291070B2 (en) 2010-12-03 2016-03-22 Pratt & Whitney Canada Corp. Gas turbine rotor containment

Also Published As

Publication number Publication date
JPS611807A (ja) 1986-01-07

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

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Effective date: 19860121

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Inventor name: AUSTREM, IVAR