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DE1291559B - Multi-stage axial turbo machine, in particular a gas turbine - Google Patents

Multi-stage axial turbo machine, in particular a gas turbine

Info

Publication number
DE1291559B
DE1291559B DE1962L0043159 DEL0043159A DE1291559B DE 1291559 B DE1291559 B DE 1291559B DE 1962L0043159 DE1962L0043159 DE 1962L0043159 DE L0043159 A DEL0043159 A DE L0043159A DE 1291559 B DE1291559 B DE 1291559B
Authority
DE
Germany
Prior art keywords
housing
gas turbine
turbo machine
stage axial
ribs
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.)
Pending
Application number
DE1962L0043159
Other languages
German (de)
Inventor
Wittstock Gerhard
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.)
Licentia Patent Verwaltungs GmbH
Original Assignee
Licentia Patent Verwaltungs 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
Priority to GB1053846D priority Critical patent/GB1053846A/en
Application filed by Licentia Patent Verwaltungs GmbH filed Critical Licentia Patent Verwaltungs GmbH
Priority to DE1962L0043159 priority patent/DE1291559B/en
Priority to CH1222463A priority patent/CH427415A/en
Publication of DE1291559B publication Critical patent/DE1291559B/en
Pending legal-status Critical Current

Links

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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Hierzu 1 Blatt Zeichnungen1 sheet of drawings

Claims (2)

Patentansprüche:Patent claims: 1. Mehrstufige Axialöirbomaschine, insbesondere -gasturbine, mit, ,Leitschaufeln, die an ihrem radial äußeren Ende durch etwa profilgleiche Durchbrüche' eines ein- oderJmehrwandigen, mit Radialrippen versehenen Gehäuses gesteckt und außerhalb dieser Durchbrüche durch ein Blechstück, das in Nuten an den Schaufelenden eingreift,, lösbar befestigt sind, d adurch gekennzeichnet, daß zwischen jeweils zwei, benachbarten Schaufeln (16) und zwischen zwei Radialrippen (20,21) des Gehäuses ein federndes Bleghstück (17) angeordnet ist, das in an diesen Rippen ausgebildete Ringnuten (18,19) axial eingreift und in Umfangsrichtung am einen Ende.jn eine Nut (22) am Bauch einer Schaufel" eingreift, während es am anderen Ende mit einer Ausnehmung (23) am Rücken der benachbarten Schaufel anliegt.1. Multi-stage axial flow machine, in particular -gas turbine, with,, guide vanes, which at their radially outer end by approximately the same profile Breakthroughs in a single or multi-walled, plugged with radial ribs housing and outside these openings through a piece of sheet metal that is in grooves on the Blade ends engaged, are releasably attached, thereby characterized in that between each two, adjacent blades (16) and a resilient sheet metal piece (17) is arranged between two radial ribs (20, 21) of the housing is, which engages in formed on these ribs annular grooves (18,19) axially and in the circumferential direction at one Ende.jn a groove (22) on the belly of a shovel "engages while it is at the the other end rests against the back of the adjacent blade with a recess (23). 2. Axialturbomaschine nach Anspruch 1, dadurch gekennzeichnet','daß die Wände (12,14) des Gehäuses satt aneinanderliegen und in an sich bekannter Weise mit radialem Abstand von einem konzentrischen Mantel (24) umgeben sind, bis zu dem sich die Radialrippen (20, 21) er-2. Axial turbo machine according to claim 1, characterized in that the walls (12, 14) of the housing lie close to each other and in a known manner with a radial distance from are surrounded by a concentric jacket (24), up to which the radial ribs (20, 21) .:.., ,strecken; :.' '.:.., ,stretch; :. ' '
DE1962L0043159 1962-10-10 1962-10-10 Multi-stage axial turbo machine, in particular a gas turbine Pending DE1291559B (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB1053846D GB1053846A (en) 1962-10-10
DE1962L0043159 DE1291559B (en) 1962-10-10 1962-10-10 Multi-stage axial turbo machine, in particular a gas turbine
CH1222463A CH427415A (en) 1962-10-10 1963-10-03 Axial turbine machine stator, in particular axial gas turbine stator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE1962L0043159 DE1291559B (en) 1962-10-10 1962-10-10 Multi-stage axial turbo machine, in particular a gas turbine

Publications (1)

Publication Number Publication Date
DE1291559B true DE1291559B (en) 1969-03-27

Family

ID=7270184

Family Applications (1)

Application Number Title Priority Date Filing Date
DE1962L0043159 Pending DE1291559B (en) 1962-10-10 1962-10-10 Multi-stage axial turbo machine, in particular a gas turbine

Country Status (3)

Country Link
CH (1) CH427415A (en)
DE (1) DE1291559B (en)
GB (1) GB1053846A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
DE2819808C1 (en) * 1977-05-05 1989-01-19 Rolls Royce Guide vane ring for the turbine of a gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2220034B (en) * 1988-06-22 1992-12-02 Rolls Royce Plc Aerodynamic loading in gas turbine engines
US5961278A (en) * 1997-12-17 1999-10-05 Pratt & Whitney Canada Inc. Housing for turbine assembly

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE823823C (en) * 1949-08-27 1951-12-06 Armstrong Siddeley Motors Ltd Gas turbine with guide vane attachment
DE830853C (en) * 1948-11-27 1952-02-07 Gen Electric Nozzle ring for turbines operating at high temperatures, especially gas turbines
GB700012A (en) * 1949-10-26 1953-11-25 Cem Comp Electro Mec Improvements in the mounting and fixing of the fixed blades of axial flow turbines and compressors
CH304835A (en) * 1952-04-08 1955-01-31 Rolls Royce Bladed construction part for turbo machines.
GB728670A (en) * 1950-08-01 1955-04-27 Rolls Royce Improvements in or relating to structural elements for turbo-machines such as compressors or turbines of gas-turbine engines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE830853C (en) * 1948-11-27 1952-02-07 Gen Electric Nozzle ring for turbines operating at high temperatures, especially gas turbines
DE823823C (en) * 1949-08-27 1951-12-06 Armstrong Siddeley Motors Ltd Gas turbine with guide vane attachment
GB700012A (en) * 1949-10-26 1953-11-25 Cem Comp Electro Mec Improvements in the mounting and fixing of the fixed blades of axial flow turbines and compressors
GB728670A (en) * 1950-08-01 1955-04-27 Rolls Royce Improvements in or relating to structural elements for turbo-machines such as compressors or turbines of gas-turbine engines
GB748912A (en) * 1950-08-01 1956-05-16 Rolls Royce Improvements in or relating to blade assemblies of compressors and turbines and likemachines
CH304835A (en) * 1952-04-08 1955-01-31 Rolls Royce Bladed construction part for turbo machines.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2819808C1 (en) * 1977-05-05 1989-01-19 Rolls Royce Guide vane ring for the turbine of a gas turbine engine
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it

Also Published As

Publication number Publication date
GB1053846A (en)
CH427415A (en) 1966-12-31

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