EP0058532A2 - Tuyère de turbine axiale - Google Patents

Tuyère de turbine axiale Download PDF

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Publication number
EP0058532A2
EP0058532A2 EP82300699A EP82300699A EP0058532A2 EP 0058532 A2 EP0058532 A2 EP 0058532A2 EP 82300699 A EP82300699 A EP 82300699A EP 82300699 A EP82300699 A EP 82300699A EP 0058532 A2 EP0058532 A2 EP 0058532A2
Authority
EP
European Patent Office
Prior art keywords
slits
nozzle
turbine
filler metals
exhaust gas
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.)
Withdrawn
Application number
EP82300699A
Other languages
German (de)
English (en)
Other versions
EP0058532A3 (fr
Inventor
Yoshitsugu Nagasaki Shipyard & Engine Works Aono
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
Original Assignee
Mitsubishi Heavy Industries 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 filed Critical Mitsubishi Heavy Industries Ltd
Publication of EP0058532A2 publication Critical patent/EP0058532A2/fr
Publication of EP0058532A3 publication Critical patent/EP0058532A3/fr
Withdrawn legal-status Critical Current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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector

Definitions

  • the present invention relates to axial flow turbines, such as an exhaust gas turbine, and particularly to nozzles for such turbines.
  • FIG. 1 A cross-section of part of an exhaust gas turbine in a conventional known exhaust gas turbine supercharger is shown in Figure 1.
  • a nozzle of the exhaust gas turbine is shown in Figure 2 in a perspective view
  • a part of an outer ring of the nozzle is shown in Figure.3 in plan view.
  • the turbine is of the axial flow type and exhaust gas from a diesel engine entering a turbine inlet casing 1 passes through the nozzle 2, then drives a turbine rotor 3 by means of the turbine blades 4 and exits through a turbine outlet casing 5.
  • the nozzle 2 is of the integral type normally used with an axial flow turbine, and it is constructed of nozzle blades 6, an inner nozzle ring 7 and an outer nozzle ring 8 as shown in Figure 2.
  • nozzle blades 6 an inner nozzle ring 7 and an outer nozzle ring 8 as shown in Figure 2.
  • stainless steel materials are used for the nozzle blades 6 because of their resistance to heat and corrosion, but the inner nozzle ring 7 and the outer nozzle ring 8 are made of cast iron with the nozzle blades 6 fixed therein.
  • expansion slits 9 as shown in Figures 2 and 3 are provided at several locations in the outer nozzle ring 8.
  • the slits 9 are formed in a rectilinear shape between the nozzle blades 6 by machining as shown in Figure 3, and thereby the outer nozzle ring 8 is divided into several segments. The size of these slits is, in the case of the nozzle of a large-sixed supercharger, about 3 mm wide and about 170 mm long.
  • the flow of gas at high pressure on the inlet side of the nozzle blades enters through the slits in the outer nozzle ring into a sealingly enclosed chamber 10, and then escapes through the same slits towards the outlet side of the nozzle blades at a low pressure.
  • the turbine inlet casing is formed as a double casing structure consisting of an inner casing 11 and an outer casing 12, and this construction is especially advantageous in that extraction of the rotor is made possible without disconnecting the coupling between the exhaust pipe of the diesel engine and the turbine inlet casing of the supercharger as shown in Figure 5.
  • a gap is provided in the exhaust duct between the said inner and outer casings to allow for the removal of the inner casing 11.
  • an integral type nozzle for use in an axial flow turbine in which nozzle a number of slits are formed in the outer nozzle ring so as to divide it into a number of segments in its circumferential direction, is characterised in that filler metals are located in the said slits so as,in use of the turbine, to prevent gas from escaping through said slits.
  • escape of exhaust gas through the slits can be prevented without carrying out any special machining of the nozzle and moreover without being influenced by thermal expansion.
  • slits 9 are formed in the outer nozzle ring 8 similarly to the prior art construction shown in Figure 2, and the width of the slits is a minimum of 2-3 mm, like the nozzles in the prior art, due to machining limitations.
  • the outer circumferential edges of the nozzle blades 6 are made integral with the outer nozzle ring 8 during casting, and filler metals 15 made of heat resisting material are inserted into the several slits 9.
  • the thickness of the filler metal 15 is made slightly thinner than the nominal width of the slits 9 so as to leave a small clearance between the opposed surfaces of the slits 9 and their filler metals 15 when fixed; thereby some adaptability for dimensional variations of the width of the slits is retained.
  • the radial depth of the filler metal 15 is somewhat shorter than the depth of the slits 9 so as not to protrude beyond the inner diameter of the outer nozzle ring 8, as shown by the dashed line in Figure 8, while for preventing the said metals 15 from being displaced, tongues 16 are provided on each filler metal and are bent down onto the outer circumference of the outer nozzle ring 8 and secured thereto by means of bolts 17.
  • the escape of exhaust gas through the slits can be prevented. Accordingly, degradation of the performance of the nozzle can be prevented.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP82300699A 1981-02-17 1982-02-12 Tuyère de turbine axiale Withdrawn EP0058532A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP20146/81U 1981-02-17
JP2014681U JPS57134302U (fr) 1981-02-17 1981-02-17

Publications (2)

Publication Number Publication Date
EP0058532A2 true EP0058532A2 (fr) 1982-08-25
EP0058532A3 EP0058532A3 (fr) 1983-04-27

Family

ID=12019006

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82300699A Withdrawn EP0058532A3 (fr) 1981-02-17 1982-02-12 Tuyère de turbine axiale

Country Status (3)

Country Link
EP (1) EP0058532A3 (fr)
JP (1) JPS57134302U (fr)
DK (1) DK48082A (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005042926A1 (fr) 2003-10-28 2005-05-12 Pratt & Whitney Canada Corp. Controle de fuite ameliore dans un moteur a turbine
DE102005062562A1 (de) * 2005-12-27 2007-06-28 Abb Turbo Systems Ag Axialturbine
CN101936193A (zh) * 2009-06-30 2011-01-05 上海电气电站设备有限公司 一种大型汽轮机整体喷嘴组的制造方法
WO2014009203A1 (fr) * 2012-07-09 2014-01-16 Abb Turbo Systems Ag Turbine à gaz d'échappement comprenant une couronne directrice fermée

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1286534A (fr) * 1961-04-21 1962-03-02 Austin Motor Co Ltd Turbine à gaz du type axial
FR1297540A (fr) * 1961-08-12 1962-06-29 Gen Electric Stator de turbine
GB1018168A (en) * 1962-12-28 1966-01-26 Gen Electric Improvements in stator assembly
CH409527A (de) * 1962-02-14 1966-03-15 Licentia Gmbh Axialturbine mit Aussengehäuse und Innengehäuse und mit einem Ringflansch im Zwischenraum
GB1126718A (en) * 1966-09-09 1968-09-11 Gen Motors Corp Gas seal between turbine parts
DE1925573A1 (de) * 1968-05-22 1969-11-27 Westinghouse Electric Corp Gasturbine der Axialbauart
DE1950812A1 (de) * 1968-10-30 1970-06-18 Westinghouse Electric Corp Waermebewegliche Dichtungsanordnung fuer Axialturbinen,vorzugsweise Axial-Gasturbinen
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
GB1348446A (en) * 1971-12-01 1974-03-20 Westinghouse Electric Corp Bladed diaphragm structure for an axial flow machine
GB1358798A (en) * 1972-06-09 1974-07-10 Bbc Sulzer Turbomaschinen Sealing element for a turbo-machine
JPS5427604A (en) * 1977-08-03 1979-03-01 Toshiba Corp Steam turbine
DE2849747A1 (de) * 1978-11-16 1980-05-29 Volkswagenwerk Ag Aus keramischen werkstoffen bestehender axial-leitschaufelkranz fuer gasturbinen
GB1580884A (en) * 1977-08-03 1980-12-10 Rolls Royce Sealing means

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1286534A (fr) * 1961-04-21 1962-03-02 Austin Motor Co Ltd Turbine à gaz du type axial
FR1297540A (fr) * 1961-08-12 1962-06-29 Gen Electric Stator de turbine
CH409527A (de) * 1962-02-14 1966-03-15 Licentia Gmbh Axialturbine mit Aussengehäuse und Innengehäuse und mit einem Ringflansch im Zwischenraum
GB1018168A (en) * 1962-12-28 1966-01-26 Gen Electric Improvements in stator assembly
GB1126718A (en) * 1966-09-09 1968-09-11 Gen Motors Corp Gas seal between turbine parts
DE1925573A1 (de) * 1968-05-22 1969-11-27 Westinghouse Electric Corp Gasturbine der Axialbauart
DE1950812A1 (de) * 1968-10-30 1970-06-18 Westinghouse Electric Corp Waermebewegliche Dichtungsanordnung fuer Axialturbinen,vorzugsweise Axial-Gasturbinen
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
GB1348446A (en) * 1971-12-01 1974-03-20 Westinghouse Electric Corp Bladed diaphragm structure for an axial flow machine
GB1358798A (en) * 1972-06-09 1974-07-10 Bbc Sulzer Turbomaschinen Sealing element for a turbo-machine
JPS5427604A (en) * 1977-08-03 1979-03-01 Toshiba Corp Steam turbine
GB1580884A (en) * 1977-08-03 1980-12-10 Rolls Royce Sealing means
DE2849747A1 (de) * 1978-11-16 1980-05-29 Volkswagenwerk Ag Aus keramischen werkstoffen bestehender axial-leitschaufelkranz fuer gasturbinen

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005042926A1 (fr) 2003-10-28 2005-05-12 Pratt & Whitney Canada Corp. Controle de fuite ameliore dans un moteur a turbine
EP1697617A1 (fr) * 2003-10-28 2006-09-06 PRATT & WHITNEY CANADA INC. Controle de fuite ameliore dans un moteur a turbine
US7128522B2 (en) 2003-10-28 2006-10-31 Pratt & Whitney Canada Corp. Leakage control in a gas turbine engine
EP1697617A4 (fr) * 2003-10-28 2009-07-22 Pratt & Whitney Canada Controle de fuite ameliore dans un moteur a turbine
DE102005062562A1 (de) * 2005-12-27 2007-06-28 Abb Turbo Systems Ag Axialturbine
CN101936193A (zh) * 2009-06-30 2011-01-05 上海电气电站设备有限公司 一种大型汽轮机整体喷嘴组的制造方法
CN101936193B (zh) * 2009-06-30 2013-07-10 上海电气电站设备有限公司 一种大型汽轮机整体喷嘴组的制造方法
WO2014009203A1 (fr) * 2012-07-09 2014-01-16 Abb Turbo Systems Ag Turbine à gaz d'échappement comprenant une couronne directrice fermée
CN104487659A (zh) * 2012-07-09 2015-04-01 Abb涡轮系统有限公司 带有封闭的喷嘴环的废气涡轮
EP2847439B1 (fr) 2012-07-09 2017-03-22 ABB Turbo Systems AG Turbine à gaz d'échappement comprenant une couronne directrice fermée
CN104487659B (zh) * 2012-07-09 2017-03-22 Abb涡轮系统有限公司 带有封闭的喷嘴环的废气涡轮

Also Published As

Publication number Publication date
EP0058532A3 (fr) 1983-04-27
DK48082A (da) 1982-08-18
JPS57134302U (fr) 1982-08-21

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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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AK Designated contracting states

Designated state(s): CH DE FR GB LI

PUAL Search report despatched

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RHK1 Main classification (correction)

Ipc: F01D 9/04

AK Designated contracting states

Designated state(s): CH DE FR GB LI

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Effective date: 19831012

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

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18D Application deemed to be withdrawn

Effective date: 19850402

RIN1 Information on inventor provided before grant (corrected)

Inventor name: AONO, YOSHITSUGUNAGASAKI SHIPYARD & ENGINE WORKS