US2453547A - Turbine construction - Google Patents

Turbine construction Download PDF

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Publication number
US2453547A
US2453547A US520067A US52006744A US2453547A US 2453547 A US2453547 A US 2453547A US 520067 A US520067 A US 520067A US 52006744 A US52006744 A US 52006744A US 2453547 A US2453547 A US 2453547A
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US
United States
Prior art keywords
housing
pins
mounting
casing
turbine
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
US520067A
Inventor
Carl R Soderberg
John A Clark
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft 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 United Aircraft Corp filed Critical United Aircraft Corp
Priority to US520067A priority Critical patent/US2453547A/en
Priority to GB32995/46A priority patent/GB618635A/en
Application granted granted Critical
Publication of US2453547A publication Critical patent/US2453547A/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Fig. 1 is a sectional view through the turbine.
  • Fig. 3 is a sectional view on line 3-3 of Fig. 1.
  • Each Din I8 supporting casing I0 is threaded at its inner end and engages with cot'nzlerating ⁇ threads I2 in the boss 36.
  • Each pin v also has a shoulder 44 cooperating with a shoulder in the boss for accurately locating the pin in the boss.
  • Each pin may have a spline 48 by which the pinls screwed into the casing during assembly.
  • the pins 28,' in addition to supporting the rear bearing mounting, may also support exhaust duct .t0 within housing I4, since as shown in Figs. ⁇ 1 and 2 the pins extend through openings 58 in the duct.
  • a slidabie connection lill between the discharge end casing l0 and the duct permits lengthwise expansion oi' basing or ducty independently of the support of these parts by pins It and 28.
  • a turbine including a housing, a rotor within the housing. a bearing mounting for one end of the rotor, and means for supporting said mounting within the housing including a number of radial pins having a slidable connection with the housing, and -being iixed within the mounting.
  • a turbine .mcmdinge Housing e casing within the housing and defining a path for power fluid spaced from said housing, a rotor within the housing, a bearing mounting within the lhousing for said rotox-,f said mounting being located in the iluid path, said mounting having a number'oi legs each having a slidable connection with Ithe housing.

Description

N0V 9, 1948- f c. R; soDERBERG TAL 2,453,547
TURBINE CONSTRUCTION Filed Jan. 28, 1944 3 Sheets-Sheet Il.A
Nov. 9, *1948. c. R. soDERERG Erm.r 2,453,547
TURBINE CONSTRUCTION s sheets-sheet 2 Fiied Jan. 28, 1944 FIG. 2
Nov. 9, 1948. c. R. SODERBERG ETAL TURBINE CONSTRUCTION Filed Jan. 28. 1944` l I4 36 t I6 30 FIG. 3
3 Sheets-Sheet 3 L .y Pitmanv Nev. 9, 1948 TUanINa coN's'rnUo'leroN Carl R. Soderberg, Weston, Mass., and .IolnrA.V
- Clark, Glastonbury, Conn., assignors to United Aircraft Corporation, East Hartford, Conn., n a corporation of Delaware application January 2s. 1944, serial N'o. .5120.007
1 The copending application of Cronstedt, Serial N0.. 486,619, led'May 11, 1943, now Patent Num- 5 claims. (ci. 253-49) ber 2,421,833 of June 10, 1947, shows a turbine which includes a casing and a rotor, both supported byfa housing. 'Ihe path for .power gas -is within the casing and out of contact with'the housing@ so that the housing remains cool; The rear bearing. around which the power gas passes is supported within the housing by radial pins extending into legs projecting from the bearing mounting and'l the casing is supported by similar pins. l'I/hese pins, which allow for radial expansionof casing and bearing mountingare fixed in the housing 4and slide in either casing or mounting. The high operating .temperature to which 'the casing and mounting are subjected during operation of the turbine may cause galling or seizing of the pins. An object of this invention is to overcome this disadvantage by hai/ing the pins slidable in the relatively cool housing. f l y `lEn this -type of turbine, the housing may be kept cool by circulating air between the casing and housing and around the exhaust duct which surrounds the bearing mounting. A feature of this invention is an arrangement by which the sup. porting pins extend through this cool space so that the parts of the pins which are slidable in the housing remain cool. f
Other objects and advantages will be apparent from the specifications and claims andfrom the accompanying drawings which illustrate an embodiment oi the invention.
Fig. 1 is a sectional view through the turbine.
Fig. 2 is a sectional view on line 2-2 of Fig. 1.
Fig. 3 is a sectional view on line 3-3 of Fig. 1.
`The turbine includes `a casing l0 and rotor I2 both supported -inia housing i4. 'I'he casing is supported by a number of radially extending pins I6, all in substantially the same plane. The casing is free to expand lengthwise within the hous- 'ing since these pins are the sole support `for the casing.
Housing lli has a head I8 which `forms part of the housing and supports a hearing sleevef20 )for the front end ofthe -turbine rotor. At the other end of the housing is a bearing mounting 22 having a bearing 2d foi .the turbine rotor. .The
\mounting 22 has a number of radially extending legs 26 engaging with radially extending support;d ing pins 28. The casing is built up of several'rings 30, each of which has a single row of vanes 3,2'. These rows of vanes alternate with cooperating rows of blades 34 on the rotor. One ring 30 has a number of bosses 36 which receive the supporting pins i6.
An inlet duct 38 together with casing -I0 and an exhaust duct lll Varound the rear mounting- 22 tor/irl` a continuous pathfior the power gas, which is within and spaced from housing il. Cooling fluid may pass through the space between the housing and ,the parts o! the turbine d ening the ,gas path to assist in cooling the housing. Both sets of pins I8 and 28 extend through the space between housing I and the parts of the turbine deerung the gas path so that cooun'g mild win pass around parts oi` each pinto assist' in keepinglthel pins cool.
Each Din I8 supporting casing I0 is threaded at its inner end and engages with cot'nzlerating` threads I2 in the boss 36. Each pin valso has a shoulder 44 cooperating with a shoulder in the boss for accurately locating the pin in the boss.
'Ihese pins are siidable within bores 46 -in housing y i4. to permit the casing to expand freely without stressing the housing. Each pin may have a spline 48 by which the pinls screwed into the casing during assembly.
' As shown in Fig. 2, each Spin 28 supporting the rear bearingmounting is threaded to engage wi-th cooperating threads 50 in the associated leg 28, of the mounting.y Each pin 28 also has a, tapering inner end 52 `iltting in a seat in the leg /for additionally supporting and locating the pins. ,The outer end of each pin 2 8 is slidable in a bore 54 inw housing Il to permit expansin of the mounting A 'without distorting the housing. A spline I8 in l each pin provides for screwing the pin into or out l. of'the leg.
The pins 28,' in addition to supporting the rear bearing mounting, may also support exhaust duct .t0 within housing I4, since as shown in Figs.` 1 and 2 the pins extend through openings 58 in the duct. A slidabie connection lill between the discharge end casing l0 and the duct permits lengthwise expansion oi' basing or ducty independently of the support of these parts by pins It and 28.
lt is to be understood that the invention is not limited to the specific embodiment herein illustrated anddescribed, but may be used in other ways without departure from its spirit as defined .by the following claims. f
i We claim: l
1. A turbine including a housing, a rotor within the housing. a bearing mounting for one end of the rotor, and means for supporting said mounting within the housing including a number of radial pins having a slidable connection with the housing, and -being iixed within the mounting.
2. A turbine including a housing, a rotor within the housing, a bearing mounting for one end of the rotor. and means for supporting said mounting Within the housing, including a number of legs, and pins slidable in said( housingand engaging said legs.
y 3. A rturbine including a housing, a rotor within the housing, a bearing mounting for one end of the rotor, and means for supporting said mounting within the housing including a number of legs housing. f
, 4. A turbine .mcmdinge Housing, e casing within the housing and defining a path for power fluid spaced from said housing, a rotor within the housing, a bearing mounting within the lhousing for said rotox-,f said mounting being located in the iluid path, said mounting having a number'oi legs each having a slidable connection with Ithe housing.
spaced from said housing, a rotor within the housfing. a bearing mounting within the housing for s i 4 said rotor. said mounting being located in the fluid pafth, said mounting having a number of legs and pins slidable in said housing and engaging said legs for supporting the mounting.
CARL R. SODERBERG. JOHN A. CLARK,
REFERENCES CITED Thefollowing 'references'are of'record in the and Pins threaded in said legs and slidable in said lo me of this patent:
UNITEJ .STATES PATENTS Number Name l Date ,1,299,7o9e Han v. Apr. s; 1919 1,693,317 mee Nev. 2v, 192s 415 1,143,362 Noble .v I1eb.25, 1930 1,889,554 f Kennedy Nov. 2p, 1932 2,232,611 Keller .'-..Feb. 1 8, 1941 FOREIGN PATENTS 2o Number A ceuntry YDate usine June 10, 1919
US520067A 1944-01-28 1944-01-28 Turbine construction Expired - Lifetime US2453547A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US520067A US2453547A (en) 1944-01-28 1944-01-28 Turbine construction
GB32995/46A GB618635A (en) 1944-01-28 1946-11-06 Improvements in or relating to turbine drives particularly for use in aircraft propulsions

Applications Claiming Priority (1)

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US520067A US2453547A (en) 1944-01-28 1944-01-28 Turbine construction

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE908254C (en) * 1949-02-17 1954-04-05 Licentia Gmbh Axial steam or gas turbine with a supporting jacket for the guide vane discs inserted into the housing
US2692724A (en) * 1942-07-02 1954-10-26 Power Jets Res & Dev Ltd Turbine rotor mounting

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB846329A (en) * 1957-12-12 1960-08-31 Napier & Son Ltd Combustion turbine power units
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1299709A (en) * 1916-03-14 1919-04-08 Elbert J Hall Internal-combustion engine.
AT76744B (en) * 1912-03-12 1919-06-10 Ljungstroems Angturbin Ab Fastening of steam turbine parts, in particular radial turbine parts, in the turbine housing or casing.
US1693317A (en) * 1927-06-01 1928-11-27 Gen Electric Method of bracing casing structures for elastic fluid turbines and the like
US1748362A (en) * 1927-11-10 1930-02-25 Noble Warren Journal bearing
US1889554A (en) * 1930-06-27 1932-11-29 Laval Steam Turbine Co Steam chest construction for steam turbines
US2232611A (en) * 1937-11-03 1941-02-18 Tech Studien Ag Guide apparatus for axial flow turbomachines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT76744B (en) * 1912-03-12 1919-06-10 Ljungstroems Angturbin Ab Fastening of steam turbine parts, in particular radial turbine parts, in the turbine housing or casing.
US1299709A (en) * 1916-03-14 1919-04-08 Elbert J Hall Internal-combustion engine.
US1693317A (en) * 1927-06-01 1928-11-27 Gen Electric Method of bracing casing structures for elastic fluid turbines and the like
US1748362A (en) * 1927-11-10 1930-02-25 Noble Warren Journal bearing
US1889554A (en) * 1930-06-27 1932-11-29 Laval Steam Turbine Co Steam chest construction for steam turbines
US2232611A (en) * 1937-11-03 1941-02-18 Tech Studien Ag Guide apparatus for axial flow turbomachines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2692724A (en) * 1942-07-02 1954-10-26 Power Jets Res & Dev Ltd Turbine rotor mounting
DE908254C (en) * 1949-02-17 1954-04-05 Licentia Gmbh Axial steam or gas turbine with a supporting jacket for the guide vane discs inserted into the housing

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