US3762833A - Inlet structure for turbomachine - Google Patents

Inlet structure for turbomachine Download PDF

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Publication number
US3762833A
US3762833A US00260235A US3762833DA US3762833A US 3762833 A US3762833 A US 3762833A US 00260235 A US00260235 A US 00260235A US 3762833D A US3762833D A US 3762833DA US 3762833 A US3762833 A US 3762833A
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US
United States
Prior art keywords
nose piece
bars
apertures
turbomachine
diffuser tube
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
US00260235A
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English (en)
Inventor
A Miller
R Miller
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.)
Carrier Corp
Elliott Turbomachinery Co Inc
Original Assignee
Carrier Corp
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 Carrier Corp filed Critical Carrier Corp
Application granted granted Critical
Publication of US3762833A publication Critical patent/US3762833A/en
Assigned to ELLIOTT TURBOMACHINERY CO., INC. reassignment ELLIOTT TURBOMACHINERY CO., INC. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: CARRIER CORPORATION, A CORP OF DEL.
Assigned to FIRST NATIONAL BANK OF CHICAGO, THE reassignment FIRST NATIONAL BANK OF CHICAGO, THE LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: ELLIOT TURBOMACHINERY CO., INC.
Assigned to CONTINENTAL BANK N.A. reassignment CONTINENTAL BANK N.A. SECURITY INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ELLIOTT TURBOMACHINERY CO., INC.
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
    • 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
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the fluid turbomachine is provided with an inlet gas flow diffuser tube.
  • the nose piece of the turbomachine is mounted within the inlet diffuser tube, in concentri cally spaced relation thereto, by a pair of supporting bars extending transversely through the nose piece, the ends of the bars being affixed to the diffuser tube.
  • the diffuser tube in conjunction with the noise piece, provides an annular passage for the inflow of gas to the turbine wheel journaled inwardly of the nose piece.
  • the nose piece is provided with integral nozzle blades positioned in the annular gas flow passage
  • a bar retaining means engages the nose piece supporting bars in their central area and is operable to deflect the bars and maintain the same in tight engagement with the nose piece.
  • This invention is directed to a novel arrangement wherein the nose piece, including the nozzle blade structure, is restrained against vibration, but such parts are permitted to freely expand and contract with changes in temperature, without creating any objectionable stresses in the parts.
  • the nose piece is mounted in the diffuser inlet tube, and maintained in concentrically spaced relation thereto, by a pair of support bars which extend through the nose piece and through the diffuser tube.
  • Bar retaining means is mounted within the nose piece, centrally thereof, and functions to stress the mounting bars by deflecting the bars in a direction axially of the nose piece.
  • the nozzle blades are formed integral with the nose piece.
  • FIG. 1 is a vertical sectional view of the turbine portion of a turbocharger embodying our invention.
  • FIG. 2 is a view taken on line 2-2 of FIG. 1.
  • FIG. 3 is a fragmentary view illustrating a slight modiflcation in the supporting bar clamp block.
  • FIG. 4 is a fragmentary view taken on line 4-4 of FIG. 1.
  • a turbine casing 10 is attached at one end to an intermediate casing 11, a portion of which is shown in FIG. 1. These casing sections are secured together as by screws 12.
  • the opposite end wall of the casing 1 is formed with a circular shouldered opening in which is mounted the flange 13 of the diffuser inlet tube 14.
  • the flange 13 is fixedly secured in the outer wall of the easing by bolts 15.
  • An inlet manifold 16 is attached to the diffuser tube 14 as by screws 17.
  • the casing 10 is formed with cored circumferentially extending passages 18 for the circulation of cooling water.
  • a shaft 20 isjournaled in the intermediate casing section 11.
  • a turbine disc or wheel 21 is fixedly secured to the shaft 20 and is formed at its periphery with turbine blades 23.
  • the turbine structure 21, 23, is positioned and dimensioned for rotation in the inner portion of the diffuser tube 14.
  • a nose piece consisting of an outer wall 25, merging at its periphery with an annular portion 27, is mounted in the diffuser tube 14, with the annular portion 27, arranged in concentrically spaced relation to the tube 14.
  • This structural arrangement is in the form of a turbocharger. Hot exhaust gases from the internal combustion engine are supplied through the manifold 16 and the passage 30 to effect rotation of the turbine.
  • the nose piece is provided with inlet nozzle blades 31, preferably formed integral therewith.
  • the nozzle blades 31 are of the form shown in FIG. 4.
  • the ends 32 are the inlet edges of the blades. It will be understood that an impeller, not shown, is attached to the opposite end of the shaft 20 and serves as the moving part of a centrifugal compressor for supplying air under pressure to the intake manifold of the engine.
  • This invention has to do with the turbomachine inlet structure including the nose piece and its mounting in the diffuser tube 14.
  • the annular portion 27 of the nose piece is formed with apertures for the reception of a pair of nose piece supporting bars 35, 36. These bars extend transversely of the nose piece through the apertures formed therein, and across the annular fluid inlet passage 30.
  • the end portions of the bars 35, 36 extend through aligned apertures formed in the diffuser tube 14.
  • One of the supporting bars extends in angular relation to the other bar of the pair.
  • the bars 35, 36 are disposed diametrically of the nose piece and the diffuser tube 14, with one bar extending in a direction perpendicular to the other bar (see FIG. 2).
  • the bar restraining means is in the form of a block 40 formed with apertures to receive the supporting bars 35, 36.
  • the block is arranged centrally in the nose piece and means is provided to move the block in a direction axially of the nose piece to flex the bars 35, 36.
  • the block 40 is formed with a stud 43 extending through an aperture formed in the outer wall 25 of the nose piece.
  • a nut 45 is threaded on the stud 43 and serves, when tightened, to draw the outer end of the block 40 against a shoulder area 47 in the outer wall 25 of the nose piece (FIG. 1).
  • the nut 45' is in the form of a sleeve nut formed with a radial flange portion 48 engaging the outer surface of the wall 25, the block 40 abutting against the inner end of the nut 45' when the same is tightened on the stud 43.
  • the bar receiving apertures in the block 40 are so arranged that when the nuts 45 or 45' are tightened to position the block 40 against the shoulder 47 or the inner end of the nut 45, the supporting bars 35, 36 are forcibly flexed in a direction axially of the nose piece, whereby the supporting bars are restrained from movement relative to the nose piece as will be apparent.
  • the force of the engagement of the bars 35, 36 with the annular portion 27 of the nose piece is such as to maintain the bars in snug contact with the nose piece during operation of the turbomachine. That is these parts are restrained against vibration.
  • the engagement between the supporting bars and the annular portion 27 is such, however, as to permit the growth between these parts because of expansion and contraction due to temperature changes.
  • the outer ends of the bars 35, 36 may be formed with apertures to receive lashing wires 50, which serve to prevent physical displacement of the bars 35, 36 in the event of fracture of the stud 43.
  • the retained supporting bars inhibit wear at the apertures in the annular portion 27 of the nose piece, by the elimination of vibration induced in prior structures by the severe hot gas pulsations.
  • the locked cross bars 35, 36 alleviate the problem of the differential growth of the hotter nose piece with the respect to the cooler diffuser tube 14.
  • the nose piece formed with the integral nozzle blades 31 eliminates the problem incident to the prior structures, wherein the nozzle blades were carried on a nozzle ring bolted to the inner end of the nose piece.
  • the nose piece structure does not include any parts which, due to failure or fracture, can come in contact with the turbine wheel 21 or the blades 23.
  • the components making up the structural arrangement of this invention are produced economically by simple machining operations.
  • An elastic fluid turbomachine comprising a casing, a diffuser tube mounted in said casing, a nose piece positioned in said tube, said nose piece being formed with an outer wall, the periphery of said outer wall merging with an annular portion spaced concentrically within said tube and forming in conjunction therewith an annular fluid inlet passage, a bladed turbine wheel journaled in said casing and disposed inwardly of the nose piece with the wheel blades in registration with said inlet passage for the impingement of fluid flow thereon, said annular portion of said nose piece being formed with a circular series of integral nozzle blades disposed in said annular fluid inlet passage, said annular portion being formed with apertures, a pair of nose piece supporting bars extending transversely of said nose piece through said apertures and through aligned apertures in said diffuser tube, one of said bars extending in angular relation to the other bar of said pair, bar retaining means cooperable with said outer wall to forcibly flex the central portions of said bars in a direction axially of

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00260235A 1972-06-06 1972-06-06 Inlet structure for turbomachine Expired - Lifetime US3762833A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US26023572A 1972-06-06 1972-06-06

Publications (1)

Publication Number Publication Date
US3762833A true US3762833A (en) 1973-10-02

Family

ID=22988343

Family Applications (1)

Application Number Title Priority Date Filing Date
US00260235A Expired - Lifetime US3762833A (en) 1972-06-06 1972-06-06 Inlet structure for turbomachine

Country Status (9)

Country Link
US (1) US3762833A (id)
JP (1) JPS522043B2 (id)
AU (1) AU459600B2 (id)
CA (1) CA974454A (id)
CH (1) CH546887A (id)
DE (1) DE2317095C3 (id)
FR (1) FR2188706A5 (id)
GB (1) GB1424552A (id)
ZA (1) ZA731195B (id)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4405738A (en) * 1982-03-05 1983-09-20 Akzona Incorporated Flame retardant additives and flame retardant polyester compositions
GB2459646A (en) * 2008-04-28 2009-11-04 Rolls Royce Plc A Fan Assembly
GB2467155A (en) * 2009-01-26 2010-07-28 Rolls Royce Plc A Fan Assembly
US20130266428A1 (en) * 2012-04-05 2013-10-10 General Electric Company Axial turbine with containment shroud

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH068374B2 (ja) * 1983-07-19 1994-02-02 電気化学工業株式会社 熱可塑性樹脂組成物
GB201517171D0 (en) * 2015-09-29 2015-11-11 Rolls Royce Plc A casing for a gas turbine engine and a method of manufacturing such a casing

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4405738A (en) * 1982-03-05 1983-09-20 Akzona Incorporated Flame retardant additives and flame retardant polyester compositions
GB2459646A (en) * 2008-04-28 2009-11-04 Rolls Royce Plc A Fan Assembly
GB2459646B (en) * 2008-04-28 2011-03-30 Rolls Royce Plc A fan assembly
US8057171B2 (en) 2008-04-28 2011-11-15 Rolls-Royce, Plc. Fan assembly
GB2467155A (en) * 2009-01-26 2010-07-28 Rolls Royce Plc A Fan Assembly
US20100189552A1 (en) * 2009-01-26 2010-07-29 Rolls-Royce Plc Fan assembly
GB2467155B (en) * 2009-01-26 2011-10-12 Rolls Royce Plc A fan assembly
US8371803B2 (en) 2009-01-26 2013-02-12 Rolls-Royce Plc Fan casing assembly
US20130266428A1 (en) * 2012-04-05 2013-10-10 General Electric Company Axial turbine with containment shroud
US9546563B2 (en) * 2012-04-05 2017-01-17 General Electric Company Axial turbine with containment shroud

Also Published As

Publication number Publication date
ZA731195B (en) 1973-11-28
AU459600B2 (en) 1975-03-27
GB1424552A (en) 1976-02-11
AU5249073A (en) 1974-08-22
JPS4930708A (id) 1974-03-19
CH546887A (de) 1974-03-15
FR2188706A5 (id) 1974-01-18
DE2317095B2 (de) 1975-03-20
CA974454A (en) 1975-09-16
DE2317095A1 (de) 1973-12-20
JPS522043B2 (id) 1977-01-19
DE2317095C3 (de) 1975-10-23

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Legal Events

Date Code Title Description
AS Assignment

Owner name: ELLIOTT TURBOMACHINERY CO., INC., A CORP OF DELAWA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST. SUBJECT TO LICENSE RECITED.;ASSIGNOR:CARRIER CORPORATION, A CORP OF DEL.;REEL/FRAME:004499/0922

Effective date: 19851220

AS Assignment

Owner name: FIRST NATIONAL BANK OF CHICAGO, THE,ILLINOIS

Free format text: LICENSE;ASSIGNOR:ELLIOT TURBOMACHINERY CO., INC.;REEL/FRAME:004940/0562

Effective date: 19871109

Owner name: FIRST NATIONAL BANK OF CHICAGO, THE, ONE FIRST NAT

Free format text: LICENSE;ASSIGNOR:ELLIOT TURBOMACHINERY CO., INC.;REEL/FRAME:004940/0562

Effective date: 19871109

AS Assignment

Owner name: CONTINENTAL BANK N.A.

Free format text: SECURITY INTEREST;ASSIGNOR:ELLIOTT TURBOMACHINERY CO., INC.;REEL/FRAME:005258/0092

Effective date: 19891212