US2066788A - Turbine - Google Patents

Turbine Download PDF

Info

Publication number
US2066788A
US2066788A US619093A US61909332A US2066788A US 2066788 A US2066788 A US 2066788A US 619093 A US619093 A US 619093A US 61909332 A US61909332 A US 61909332A US 2066788 A US2066788 A US 2066788A
Authority
US
United States
Prior art keywords
turbine
motive
motive fluid
chamber
high temperature
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
US619093A
Other languages
English (en)
Inventor
Lysholm Alf
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.)
Milo AB
Original Assignee
Individual
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 Individual filed Critical Individual
Application granted granted Critical
Publication of US2066788A publication Critical patent/US2066788A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F01D1/28—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially radially
    • 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
    • F01D25/005—Selecting particular materials
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Definitions

  • the present invention relates to turbines adaptedto be operated by high temperature motive uids such as very highly super-heated steam and/or combustion gases. More particularly the invention relates 'to turbines having central admission of motive uid to the blading of the turbine and still more particularly, the invention relates to turbines of the radial flow type.
  • the primary object of the present invention is Y to improve upon prior forms of turbines and to provide a turbine in which high temperature motive uid is admittedto the inlet of the turbine blading without subjecting the turbine parts adjacent to the inlet conduit to excessive temperatures and without resorting to the use of a separate cooling agent.
  • the motive fluid supplied to the turbine is supplied thereto in separate streams, one of which is at high temperature and the other of which is at a relatively lower temperature, the latter stream being employed,A to afford the desired protection to certain of the turbine parts against the temperatures of the high temperature stream of motive fluid.
  • the two streams of motive fluid are maintained In substantially separated state to a point adjacent to the inlet of the turbine blading and are then mixed and delivered to the blade system of the turbine for expansion therein.
  • the invention has particular utility in connection with gas turbines, that is, turbines intended to be operated by high temperature motive fluid consisting wholly or in part of combustion gases. It is also particularly applicable to radial flow turbines ofthe type having a censuing description thereof.
  • Fig. 1 is a more or less diagrammatic longitudinal half section of a double rotation radial flow turbine embodying the invention and Fig. 2 is a similar view of another form of the 20 same type of turbine.
  • the reference character A represents the axis of rotation of the turbine with respect to which the turbine is substantially symmetrical.
  • the turbine comprises 25 two oppositehr rotating shafts Ill and II journailed in bearings I2 and I3 supported in a stationary turbine part Il.
  • Shafts I0 and II carry at their inner ends the turbine discs I5 and I6 respectively, these discs in turn carrying a plu- 30 rality of interleaved blade rings I1 and" I8 which form a radial ilow blade system.
  • a central admission chamber I9 for motive fluid.
  • Discs I5 and I6 are perforat- 35 ed as at 20 and 2l to provide passages for flow of motive uid to the centraladmission chamber I9 and the annular shaft parts 22 and 23 are perforated at 2l and 25 to permit motive fluid to now into the portion of the chamber I9 situated axi- 40 ally between the adjacent ends of the shafts.
  • Parts 32 and 33 support the axially outer plates 36 and 3l of two radially extending labyrinth 5l packings 38 and 39, the inner plates 40 and 4
  • the stationary turbine parts 28, 29, 32 and 33 provide'annular chambers 42 and 43 and within these chambers are respectively situated the hollow distributing members 44 and 45.
  • the distributing members 44 and 45 are preferably annular in form and are provided with outlets directed toward the apertures 20 and 2
  • the outlets are advantageously provided with a plurality of guide blades 46 and i 41 for directing motive fluid in the desired direction toward the apertures in the turbine discs.
  • the distributing members 44 and 45 are movably mounted with respect to the stationary parts of the turbine and are preferably held in position by a plurality of radially arranged studs, one of which is indicated at 48. It will be observed that the distributing members are spaced from the walls dening the chambers 42 and 43 and the movable mounting of the' distributing members permits them to expand and contract freely under the influence of variations in temperature.
  • Motive fluid may be conducted to each of the distributing chambers through one or a number of supply pipes, which pipes maybe arranged in the same longitudinal plane or staggered with respect to each other.
  • supply pipes which pipes maybe arranged in the same longitudinal plane or staggered with respect to each other.
  • one admission pipe is shown for each distributing member and the admission pipes are shown in staggered arrangement.
  • Each of the chambers 42 and 43 is provided with admission pipes corresponding in number and arrangement to the admission pipes delivering motive fluid to the distributing chambers.
  • motive iluid is admitted to chamber 42 by the admission pipe 49, the inner end of which is secured to the flange 30 of part 28 and motive fluid is admitted to chamber 43 by pipe 50, the inner end of which is secured to the flange 3
  • 4 has been shown as comprising axially spaced web portions
  • Pipes 49 and 50 extend through the portion
  • Motive fluid is admitted to distributing chamber 44 through an admission pipe 5
  • is advantageously centered with respect to pipe 49 by a plurality of lugs 52 fixed to one of the pipes and slidable with respect to the other to permit relative longitudinal movement between the pipes.
  • and arranged within pipe 50 serves to admit motive fluid to the distributing member 45.
  • and 53 are made of heat resistant material which is capable of withstanding extremely high temperatures without deterioration.
  • an alloy such as Silcrome, containing chromium, silicon and aluminum is suitable.
  • Shields 54 and 55 are preferably mounted in apertures 20 and 2
  • Motive fluid of relatively low temperature is supplied to the admission conduit 49 through the inlet 56 and high temperature motive fluid is supplied through the admission pipe 5
  • an arrangement for supplying motive fluid comprising combustion gases has been shown diagrammatically.
  • the inlet 56 is connected to a suitable source of air or gas at relatively low temperature and fuel is injected through pipe 51 to the nozzle 58, which fuel by combustion with the air or gas entering pipe 5
  • and motive fluid of lower temperature to pipe 49 is subject to wide variation.
  • the temperature may, for example, be from 1300 F. to 1450 F. or even higher.
  • the motive fluid is dividedy into two separate streams, one of which is heated to a high temperature and the other of which is at relatively lower temperature.
  • the high temperature stream is conducted through a conduit comprising the pipe or pipes 5
  • the motive fluid of lower temperature flows through this latter conduit and forms an insulating medium preventing the stationary parts of the turbine through which the inner conduit passes from overheating due to the high temperature motive fluid Within the inner conduit.
  • the motive fluid in the outer conduit absorbs a certain amount of heat from the walls of the inner conduit thus tending to cool the latter to some extent but the temperature of the motive fluid in the outer con- 'duit is maintained at a relatively low value because of the rapidity of flow of fluid therethrough; 'I'he heat absorbed by the motive fluid in the outer conduit is not lost because of the fact that this motive fluid, together with the high temperature motive fluid, is finally delivered to the admission chamber
  • the channels provided between shields 54 ⁇ and 55 and the adjacent portions of the aperture walls provide protection for the walls of the apertures which would otherwise be impinged by the high temperature combustion gases as they flow from' the aoeavss outlets of the distributing members into the rst blade ring of the turbine bieding.
  • FIG. 2 another form of turbine is illustrated in which the general form of construction is similar to that described' in connection with Fig. 1.
  • Like reference characters designate like parts in the two figures.
  • the admission pipes 49, 50, 5I and 53 are arranged inthe same lon gitudinal plane and the pipes and 53 instead of being slidably mounted within pipes 49 and 50 are xed relative thereto and connected to the distributing members 44 and 45 by means of suitable slip joints 5S and 60 so as to permit the necessary freedom of movement to compensate for expansion and contraction of the parts.
  • the apertures 20 and 2l in the turbine discs have mounted therein tubular shields 54a. and 55a which serve to completely protect the walls of the apertures from impingement by high temperature motive uid and which advantageously may be shaped to providenozzles for directing the high ternperature motive fluid into the ilrst blade ring of the blade system.
  • This arrangement assists in preventing the conduction of heat from the high temperature motive iluid to those rotating parts of the turbine which are not well adapted to withstand high temperatures and is particularly useful in protecting the inner shaft parts from excessive temperatures.
  • Shields 54a and 55a are made c-f high temperature resistant material.
  • the high temperature motive fluid supplied to the distributing members and the motive uid of lower temperature supplied to the space surrounding these chambers may be derived from different sources, in which event the inner and outer admission pipes will be entirely separated from each other.
  • the two streams of motive uid are derived from different sources, it will be evident that they may comprise different gases.
  • the two streams of motive 'iiuid of different temperature should be at substantially the same pressure. It is advantageous to have the motive fluid of lower temperature at a pressure slightly in excess of the pressure of the high temperature motive uid in order to prevent a possibility of leakage of the high temperature motive uid to the space or spaces surrounding the channel through which it is admitted to the inlet of the turbine blading.
  • stationary turbine parts moving parts providing a blade system having an inlet for motive fluid, some of said parts providing a chamber for full admission of motive uid to said blade system, a conduit for conducting high temperature motive iiuid to said chamber and means for conducting motive uid of lower temperature to said chamber separately from the high temperature motive iluid and in a stream enveloping said conduit and insulating the parts of the turbine between the exterior thereof and said chamber from the high temperature motive fluid.
  • aradial flow turbine having a blade system andl a central admission chamber for full admission of motive fluid to the inlet of said blade system
  • means for conducting motive fluid to said central admission chamber comprising a conduit extending from the exterior of the turbine to said chamber and a second conduit enveloping the rst named conduit and extending from the exterior of the turbine to said chamber, the rst mentioned conduit conducting high temperature motive fluid to said chamber and the second conduit conducting motive fluid of lower temperature .to said chamber in'an envelope protecting the turbine parts adjacent to said conduits from the heat of the high temperature motive uid.
  • a casing means providing a blade system having an inlet for full admission of motive iluid to moving turbine blading located near the axis of rotation of the turbine, stationary turbine parts, stationary means for continuously conducting motive uid to said blade system comprising an open unregulatedl conduit for high temperature motive fluid extending fromthe exterior of the casing to a place adjacent to said inlet and spaced from said stationary turbine parts, and means for continuously conducting an envelope of motive uid of lower temperature through the space between said conduit and said stationary parts to protect the stationary parts from contact with-the high temperature motive uid, said conduit and said space being in communication with said inlet adjacent thereto to permit the high temperature motive fluid and the low. temperature motive fluid to enter said blade system.
  • a casing means providing a blade system having an inlet for full admission of motive fluid to moving turbine blading located nearthe axis of rotation of the turbine, sta.- tionary turbine parts, stationary means for continuously conducting motive uid to said lblade system comprising an open unregulated conduit for high temperature motive fluid extending from the exterior of the casing to a place adjacent to said inlet and spaced from said stationary turbinel parts, said conduit comprising a hollow annular distributing member for motive fluid mounted to permit freedom of expansion and contraction of the distributing member within the turbine casing and non-rotatably mounted with respect to said stationary parts, and means for continuously conducting motive fluid of lower temperature to the space between said distributing member and said stationary parts, the outlets of said distributing member and of said space being in communication with said inlet adjacent to the inlet to permit the high temperature motive fluid and the low temperature motive fluid to enter said blade system, and said outlets being arranged so that the fluid emitted from said space envelopes the fluid emitted from said member
  • a blade system having an inlet adjacent to the axis of rotation of the turbine, an outer casing, a central admission chamber for full admission of motive fluid through said inlet to the moving blading of the turbine, stationary turbine parts defining a channel for flow of motive fluid of relatively low temperature extending from said casing to said chamber and a conduit within said channel and spaced from the walls thereof, said conduit extending to a place adjacent to said inlet for conducting high temperature motive fluid thereto in a stream insulated from said stationary turbine parts and enveloped by the relatively low temperature motive fluid in said channel.
  • a blade system having an inlet adjacent to the axis of rotation of the turbine, an outer casing, a central admission chamber for full admission of motive fluid through said inlet to the moving blading of the turbine, stationary turbine parts defining a channel for ow of motive fluid of relatively low temperature extending from said casing to said chamber and a conduit within said channel and spaced from the Walls thereof, said conduit extending to a place adjacent to said inlet for. conducting high temperature motive fluid thereto in a stream insulated from said stationary turbine parts and enveloped by the relatively low temperature motive fluid in said channel, said conduit being movably mounted to permit expansion and contraction thereof relative to said stationary turbine parts.
  • a radial flow turbine having a central admission chamber, a shaft, a blade-carrying disc fixed to said shaft, stationary turbine parts around said shaft ⁇ providing a chamber around said shaft', a distributing member for motive fluid within said second mentioned chamber and spaced from the walls thereof, a conduit for conducting motive fluid of relatively low temperature to said second mentioned chamber, a second conduit for conducting high temperature motive fluid to said distributing' member, said second mentioned conduit being within said first mentioned conduit and spaced therefrom and said second mentioned chamber and said distributing member having outlets in communication With said central admission chamber.
  • a radial flow turbine having a central admission chamber, a shaft, a blade-carrying disc fixed to said shaft, stationary turbine parts around said shaft providing a chamber around said shaft, a distributing member for motive fluid movably mounted Within said second mentioned chamber and spaced from the walls thereof, a conduit for conducting motive fluid of relatively low temperature to said second mentioned chamber, a second conduit for conducting high temperature motive fluid to said distributing member, said second mentioned conduit being movably mounted within said first mentioned conduit and spaced therefrom and said second mentioned chamber and said distributing member having outlets in communication with said central admission chamber.
  • a radial flow turbine of the double rotation type two shafts adapted to rotate in opposite directions, apertured turbine discs carried by said shafts, each of said discs carrying a plurality of radial flow blade rings providing a radial flow blade system, there being a central admission chamber radially within said blade system, stationary turbine parts providing annular chambers around each of said shafts and situated axially outside of said discs, the apertures in said turbine discs providing communication between the central admission chamber and said annular chambers, a distributing member for motive fluid situated in each of said annular chambers and spaced from the walls thereof, conduits for delivering motive fluid of relatively low temperature to said annular chambers and conduits for delivering high temperature motive fluid to said distributing members, said last mentioned conduits being within the first mentioned conduits and spaced therefrom and said distributing members having outlets for delivering high temperature motive fluid through the apertures in said discs to said central admission chamber.
  • a radial flow turbine of the double rotation type two shafts adapted to rotate in opposite directions, apertured turbine discs carried by said shafts, each of said discs carrying a plurality of radial flow blade rings providing a radial flow blade system, there being a central admission chamber located axially between said shafts and radially within said blade system, stationary turbine parts providing annularchambers around each of said shafts and situated axially outside of said discs, said annular chambers being in communication with said central admission chamber through apertures in said shafts, a distributing member for motive fluid situated in each of said annular chambers and spaced from the walls thereof, a conduit for delivering motive fluid of relatively low temperature to each of said annular chambers and a conduit for delivering high temperature motive fluid to each of said distributing members, said last mentioned conduit being within the first mentioned conduit and spaced therefrom and said distributing members having outlets for delivering high temperature motive fluid through the apertures in said discs to said central admission chamber.
  • a radial flow elastic fluid turbine comprising oppositely rotating shafts, discs carried by each of said shafts and carrying a plurality of blade rings forming a radial flow blade system, said discs having apertures therein radially inwardly of said blade system and there being a central admission chamber axially between said discs, stationary turbine parts providing annular chambers around said shafts axially outside of 'said discs, radially extendingv labyrinth packing between said discs and certain of said stationary turbine parts, said labyrinth packing being in communication with said annular chambers, distributing members for motive fluid mounted in each of said annular chambers and spaced from the walls thereof, means for conducting high temperature motive fluid to each of said distributing members and' means for conducting motive fluid of lower temperature to each of said annular chambers, said first mentioned means being within and spaced from said second mentioned means, said distributing members having outlets for directing highftemperature motive fluid through the apertures in'said discs and said annular chambers delivering motive fluid of lower temperature through
  • a shaft a blade-carrying rotor disc mounted on said shaft and having a plurality of apertures therein for passage of motive fluid through the disc radially outwardly of said shaft to the inlet of the turbine blading, shields extending through said apertures and spaced from the walls thereof, means for supplying motive fluid of relatively low temperature to said in- ⁇ let through said apertures to one side of said shields and means for supplying high temperature motive uid to said inlet through said apertures on the opposite side of said shields, the relatively cool motive fluid flowing through the spaces between the shields and the adjacent portions of the walls of the apertures.
  • a shaft a blade-carrying rotor disc mounted on said shaft and having a plurality of apertures therein for passage of motive iiuid through the disc radially outwardly of said c shaft to the inlet of the turbine blading, tubular shields extending through said apertures and spaced from the walls thereof, means forsupplying high temperature motive fluid to said inlet through said shields, and means for supplying motive uid of relatively lower temperature through the spaces provided between the shields and the walls of said apertures.
  • a blade-carrying rotor dis having apertures therein for passage of motive uid through the disc to the inlet of the turbine blading, stationary turbine parts providing a chamber in communicationwith said apertures for admission of motive fluid of relatively 10W temperature and a distributing member for high temperature motive uid situated in said chamber and spaced from the walls thereof, said distributing member having an outlet for discharging high temperature motive iiuid through said apertures and there being guide blades in said outlet.
  • a blade system In a turbine, a blade system, parts forming an admission chamber for said blade system, parts forming a second chamber for admission of motive uid of relatively low temperature to said admission chamber, a distributing member for high temperature motive fluid located in said second chamber and spaced from the walls thereof, said distributing member having an outlet in communication with said admission chamber and guide bladesin said outlet.
  • stationary turbine parts forming a chamber for motive uid of relatively'low temperature, an admission pipe communicating with said chamber, a distributing member for high temperaturei'motive iiuid movably mounted temperature, an admission pipe communicating with said chamber, a distributing member for high temperature motive 'iiuid movably mounted insaid chamber and spaced from the walls thereof, a second admission pipe communicating with said distributing member, said second admission pipe being fixed within said first mentioned admission pipe and spaced therefrom, and means providing a joint permitting relative movement between said second admission pipe and said distributing member.
  • a turbine having a central admission chamber, a shaft, a blade-carrying rotor disc on said shaft, stationary turbine parts, packing between the shaft andv the stationary parts axially to one side of the disc, labyrinth packing between the disc and the stationary parts, said labyrinth packing being on Athe same side of the disc as the shaft packing and means for conducting motive fluid to said central admission chamber comprising an inner channel for high temperature motive fluid and an outer channel for low temperature motive fluid enveloping the inner channel, said channels passing between said packings and the outer channel being in communication therewith.
  • a radial iow turbine of the double rotation type having a central admission chamber, two opposltely rotatable shafts, rotor discs on said shafts, said discs being adapted to rotate in opposite directions and carrying blades forming a, radial ow blade system to which motive uid v is admitted from said central admission chamber,
  • a radial flow elastic uid turbine comprising oppositely rotating shafts, discs carried by each of said shafts and carrying a plurality of blade rings forming a radial iow Yblade system, said discs having apertures therein radially inwardly of said blade system and there being a central admission chamber axially between said discs, and means for conducting motive fluid from the exterior of the turbine to said apertures comprising inner conduits for high temperature motive uid and an outer conduit enveloping each of the inner conduits for conducting low temperature motive uid, whereby to protect the turbine parts adjacent to the inner conduits from the heat of the high temperature motive fluid.
  • a rotor comprising a shaft and turbine blades including a blade row of relatively small diameter having an inlet for full admission of motive iuid to the turbine blading, stationary'turbine parts providing a chamber around said shaft axially to one side of said inlet and in communication therewith, a stationary hollow distributing member for high temperature motive fluid located in said chamber and spaced from the walls thereof, said distributing member having an outlet at the side ,thereof adjacent to said inlet for supplying, said high temperature motive fluid to the turbine blading. andA said chamber having an inlet for relatively low temperature motive fluid.
  • a rotor comprising a shaft and turbine blading including a blade row of relatively small diameter having an inlet for full admission of motive fluid to the turbine blading, stationary turbine parts providing a chamber around said shaft axially to one side of said inlet and in communication therewith, a hollow distributing member for high temperature motive fluid located in said chamber and spaced from the walls thereof, said distributing member having an outlet at the side thereof adjacent to said inlet for supplying said high temperature motive fluid to the turbine blading and said chamber having an inlet for relatively low temperature motive uid, and radially extending stationary guide blades for guiding motive iluid discharged from the outlet of said distributing member.
  • a rotor comprising a shaft and turbine blading including a blade row of relatively small diameter having an inlet for full admission of motive fluid to the turbine blading, stationary turbine parts providing a chamber around said shaft axially to one side of said inlet and in communication therewith, packing around the shaft for preventing leakage of fluid from said chamber, and a hollow distributing member for high temperature fluid located in said chamber and spaced from the walls thereof.
  • said distributing member having an outlet at the side thereof adjacent to said inlet for supplying said high temperature motive fluid to the turbine blading, and said chamber having an inlet for admitting relatively low temperature motive uid to the space in said chamber around said distributing member whereby to protect said stationary turbine parts and said packing from the heat of the high temperature motive fluid in the distributing member.
  • a rotor comprising a shaft and turbine blading including a blade row of relatively small diameter having an inlet for full admission of motive fluid to the turbineblading, stationary turbine parts providing a chamber around said shaft axially to one side of said inlet and in vcommunication therewith, a stationary hollow annular distributing member for high temperature motive fluid located in said chamber and extending around said shaft and spaced from the walls of the chamber and from the shaft, said distributing member having an outlet at the side thereof adjacent to said inlet for supplying said high temperature motive Iiuid to the turbine blading and said chamber having an inlet for admitting relatively low temperature motive iluid to the space in said chamber around said distributing member whereby to protect said stationary turbine parts from the heat of the high temperature motive fluid in the distributing member.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US619093A 1931-09-14 1932-06-24 Turbine Expired - Lifetime US2066788A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE382547X 1931-09-14

Publications (1)

Publication Number Publication Date
US2066788A true US2066788A (en) 1937-01-05

Family

ID=6359644

Family Applications (1)

Application Number Title Priority Date Filing Date
US619093A Expired - Lifetime US2066788A (en) 1931-09-14 1932-06-24 Turbine

Country Status (4)

Country Link
US (1) US2066788A (enrdf_load_stackoverflow)
FR (1) FR742787A (enrdf_load_stackoverflow)
GB (1) GB382547A (enrdf_load_stackoverflow)
NL (1) NL34915C (enrdf_load_stackoverflow)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2439473A (en) * 1943-05-11 1948-04-13 United Aireraft Corp Pressurized protective conduit for hot gas power plants
US2458066A (en) * 1944-07-20 1949-01-04 American Locomotive Co Combustion chamber
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US2743579A (en) * 1950-11-02 1956-05-01 Gen Motors Corp Gas turbine engine with turbine nozzle cooled by combustion chamber jacket air
US2873909A (en) * 1954-10-26 1959-02-17 Svenska Rotor Maskiner Ab Rotary devices and casing structures therefor
LU91970B1 (fr) * 2012-04-03 2013-10-04 Equitherm S A R L Turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE767491C (de) * 1935-12-09 1952-09-08 Anxionnaz Rene Waermekraftanlage mit Gasturbinen mit Gleichdruckverbrennung

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2439473A (en) * 1943-05-11 1948-04-13 United Aireraft Corp Pressurized protective conduit for hot gas power plants
US2458066A (en) * 1944-07-20 1949-01-04 American Locomotive Co Combustion chamber
US2608057A (en) * 1949-12-24 1952-08-26 A V Roe Canada Ltd Gas turbine nozzle box
US2743579A (en) * 1950-11-02 1956-05-01 Gen Motors Corp Gas turbine engine with turbine nozzle cooled by combustion chamber jacket air
US2873909A (en) * 1954-10-26 1959-02-17 Svenska Rotor Maskiner Ab Rotary devices and casing structures therefor
LU91970B1 (fr) * 2012-04-03 2013-10-04 Equitherm S A R L Turbine
WO2013150034A1 (en) * 2012-04-03 2013-10-10 Equitherm S.À R.L. Turbine
US9840915B2 (en) 2012-04-03 2017-12-12 Equitherm S.À R.L. Turbine

Also Published As

Publication number Publication date
NL34915C (enrdf_load_stackoverflow)
GB382547A (en) 1932-10-27
FR742787A (enrdf_load_stackoverflow) 1933-03-15

Similar Documents

Publication Publication Date Title
US1960810A (en) Gas turbine
US2080425A (en) Turbine
US2244467A (en) Turbine
US3312448A (en) Seal arrangement for preventing leakage of lubricant in gas turbine engines
US2241782A (en) Gas turbine
US4101242A (en) Matching thermal expansion of components of turbo-machines
US3275294A (en) Elastic fluid apparatus
US2650753A (en) Turbomachine stator casing
US3453825A (en) Gas turbine engine having turbine discs with reduced temperature differential
US2823891A (en) Steam turbine
US2282894A (en) Elastic fluid turbine
US2552239A (en) Turbine rotor cooling arrangement
US4804310A (en) Clearance control apparatus for a bladed fluid flow machine
US3605412A (en) Fluid cooled thrust nozzle for a rocket
US2078957A (en) Gas turbine apparatus
US2066788A (en) Turbine
US2333053A (en) High temperature elastic fluid turbine
US2304994A (en) Turbine cylinder cooling
US3300178A (en) Turbines
US1820725A (en) Elastic fluid turbine
US2467818A (en) High-temperature turbine casing arrangement
US2891382A (en) Liquid-cooled turbine
US3657884A (en) Trans-nozzle steam injection gas turbine
US2451261A (en) High and low pressure turbine rotor cooling arrangement
GB677274A (en) Improvements in and relating to gas turbine nozzle structures