US2467168A - High-temperature turbomachine - Google Patents

High-temperature turbomachine Download PDF

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Publication number
US2467168A
US2467168A US583163A US58316345A US2467168A US 2467168 A US2467168 A US 2467168A US 583163 A US583163 A US 583163A US 58316345 A US58316345 A US 58316345A US 2467168 A US2467168 A US 2467168A
Authority
US
United States
Prior art keywords
sectors
blades
wall
sector
division
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.)
Expired - Lifetime
Application number
US583163A
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English (en)
Inventor
Traupel Walter
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.)
Sulzer AG
Original Assignee
Sulzer AG
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 Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US2467168A publication Critical patent/US2467168A/en
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
    • F01D9/02—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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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

Definitions

  • This invention relates to turbo-machines and in particular to such machines operated by a high temperature working medium and constructed to include at least one stationary interstage division wall supported in the machine by guide blades.
  • the invention consists in that the-wall is divided into at least four sectors,
  • the invention stems from the discovery that inthe guide blades which carry the division walls considerably higher peak stresses arise when the walls are divided, according to common practice, into two half discs only, than when they are divided into at least four sectors.
  • the explanation of this unexpected phenomenon is to -be sought in the fact that, when the walls are dvided into two halves, the centre ocr the pressure loading on each half disc ris so unfavourably placed with regard to the guide blades that, on account of the resulting undulating distortion of the half walls, some of the blades are loaded in a direction contrary to the loading of the others.
  • the differently directed bending stresses Winch thus present themselves in 'the individual blades, maximum stresses arising in particular blades may take on inadmissibly high values.
  • the division wall is divided up into at least four sectors.
  • the distribution of the bending stress over the guide blades carrying the single sectors then becomes so nearly uniform that each of the blades is subjected to stressing of approximately the same force and always in the same direction. Abnormally high loading of single blades is thus prevented.
  • the sectors of the division wall prefferent for the sectors of the division wall to be so designed that the edges in contact with each other are capable of mutual displacement. Such edges may, for instance, engage with each other by means of tongues and grooves.
  • the guide blades may be connected to the sectors of the division wall either by riveting or by welding.
  • Fig. 1 is a longitudinal section through the complete turbo-machine
  • Fig. 2 is a cross-section on the line II-II of Fig. 1;
  • Fig. 3 is a cross-section on the line III-lII 0f Fig. 2;
  • Fig. 4 is a perspective of a group of guide blades with attached division wall sector and intermediate piece
  • Fig. 5 is a perspective of one of the wall sectors.
  • Fig. 6 is a perspective of one of the intermediate pieces.
  • the casing of the turbo-machine consists of two parts I and 2 which are held together with the aid of the flanges 3 and 4.
  • the working medium ows to the casing through the-pipe 5 and is led of! again through the pipe 6.
  • the lower part I of the casing carries the bearings 1 and 8, in which the rotor 9 lies.
  • The' shaft 6' and the discs 1', l' and 9' of the rotor are made in one piece by forging and subsequent machining.
  • To the discs 1', 8' and 9' are attached the rotor'. blading sets I0, Il and I2.
  • each wall is divided 'into six U-shaped sectors 25, as illustrated particularly in Figs.2, 4 and 5.
  • Each of the six sectors making up the division wail I5, for example, is held by seven of the guide blades I3.
  • Each guide blade carries at its innen end a rivet I9 by means of which the attached sector of the division wall, in the form of a hollow body, is connected to it.
  • the tongues I8 are insertable in the spaces 30 and bridge the spaces of the adjacent sectors 25.
  • the several wall sectors 25 are substantially identical, but assembly is facilitated if the intermediate pieces 20 are constructed so that one sector carries two tongues I8, one sector, none, and all the rest of the sectors, one. In this way a gastight seal is provided in which the edge of the one sector can be displaced relatively to the edge of the other sector, for instance when the wall is bent or expands from heating.
  • the guide blades are first attached by riveting to the U-shaped body of the wall sectors.
  • the body of the sector is partly closed by an intermediate piece 20 which is attached by the rivets 2
  • Part of the intermediate piece 20. which projects beyond the edge I'I of the sector, thm forms the tonguel.
  • the feet 28 of the blades are inserted in groovesof the casing 29 and held by the caulking rings 22, 23.
  • the inner peripheral surfaces of the intermediate pieces 20 have V-shaped grooves 3
  • pressors may be manufactured as proposed in the invention.
  • the inventionv offers special advantages inv ⁇ machines fom ⁇ hot working medium in which the division walls are particularly heavily stressed.
  • turbo-machines for operating at high temperatures, the improvement which comprises a housing, several rows of guide blades fixed at their exterior peripheries to the housing, a. rotor 15 1,293,564

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)
US583163A 1944-07-05 1945-03-16 High-temperature turbomachine Expired - Lifetime US2467168A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH2467168X 1944-07-05

Publications (1)

Publication Number Publication Date
US2467168A true US2467168A (en) 1949-04-12

Family

ID=4569462

Family Applications (1)

Application Number Title Priority Date Filing Date
US583163A Expired - Lifetime US2467168A (en) 1944-07-05 1945-03-16 High-temperature turbomachine

Country Status (5)

Country Link
US (1) US2467168A (fr)
BE (1) BE458908A (fr)
CH (1) CH241738A (fr)
FR (1) FR911549A (fr)
NL (2) NL118815B (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2724545A (en) * 1949-12-05 1955-11-22 Tech Studien Ag Discharge casings for axial flow engines
US2772069A (en) * 1951-10-31 1956-11-27 Gen Motors Corp Segmented stator ring assembly
US2945673A (en) * 1951-10-31 1960-07-19 Gen Motors Corp Segmented stator ring assembly
US2997275A (en) * 1959-03-23 1961-08-22 Westinghouse Electric Corp Stator structure for axial-flow fluid machine
US3412977A (en) * 1965-04-15 1968-11-26 Gen Electric Segmented annular sealing ring and method of its manufacture

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190726088A (en) * 1907-11-26 1908-09-24 Frederick Stanley Cox Improvements in Drop-down Ejector Small-arms.
US1070309A (en) * 1912-12-13 1913-08-12 Southwark Foundry & Machine Co Steam-turbine.
US1298564A (en) * 1918-06-12 1919-03-25 Gen Electric Elastic-fluid turbine.
US1641665A (en) * 1925-11-21 1927-09-06 Gen Electric Turbine-nozzle diaphragm
US2350309A (en) * 1940-09-12 1944-05-30 Allis Chalmers Mfg Co Blade shrouding

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190726088A (en) * 1907-11-26 1908-09-24 Frederick Stanley Cox Improvements in Drop-down Ejector Small-arms.
US1070309A (en) * 1912-12-13 1913-08-12 Southwark Foundry & Machine Co Steam-turbine.
US1298564A (en) * 1918-06-12 1919-03-25 Gen Electric Elastic-fluid turbine.
US1641665A (en) * 1925-11-21 1927-09-06 Gen Electric Turbine-nozzle diaphragm
US2350309A (en) * 1940-09-12 1944-05-30 Allis Chalmers Mfg Co Blade shrouding

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2724545A (en) * 1949-12-05 1955-11-22 Tech Studien Ag Discharge casings for axial flow engines
US2772069A (en) * 1951-10-31 1956-11-27 Gen Motors Corp Segmented stator ring assembly
US2945673A (en) * 1951-10-31 1960-07-19 Gen Motors Corp Segmented stator ring assembly
US2997275A (en) * 1959-03-23 1961-08-22 Westinghouse Electric Corp Stator structure for axial-flow fluid machine
US3412977A (en) * 1965-04-15 1968-11-26 Gen Electric Segmented annular sealing ring and method of its manufacture

Also Published As

Publication number Publication date
FR911549A (fr) 1946-07-10
NL60257C (fr)
CH241738A (de) 1946-03-31
NL118815B (fr)
BE458908A (fr)

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