US2276563A - Elastic fluid turbine - Google Patents

Elastic fluid turbine Download PDF

Info

Publication number
US2276563A
US2276563A US322194A US32219440A US2276563A US 2276563 A US2276563 A US 2276563A US 322194 A US322194 A US 322194A US 32219440 A US32219440 A US 32219440A US 2276563 A US2276563 A US 2276563A
Authority
US
United States
Prior art keywords
rotor
blades
stator
conoidal
section
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
US322194A
Other languages
English (en)
Inventor
Cook Stanley Smith
Douglas Louis Mortimer
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.)
PARSONS MARINE STEAM TURBINE
PARSONS MARINE STEAM TURBINE COMPANY Ltd
Original Assignee
PARSONS MARINE STEAM TURBINE
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 PARSONS MARINE STEAM TURBINE filed Critical PARSONS MARINE STEAM TURBINE
Application granted granted Critical
Publication of US2276563A publication Critical patent/US2276563A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/02—Machines or engines with axial-thrust balancing effected by working-fluid characterised by having one fluid flow in one axial direction and another fluid flow in the opposite direction

Definitions

  • This invention relates to elastic fluid turbines of the double flow type in which the direction of flow is in opposite directions in the two sections. 7
  • the duplicate flows are usually similar in every respect and symmetrically disposed about a transverse plane at mid length.
  • the main object of the present invention is to provide constructions in which the clearance may be reduced without impairing safety.
  • the invention in brief consists in a double flow elastic fluid turbine of the type described in one flow portion of which the rotor blade tips lie in a conoidal surface, in the other flow portion the stator blade tips lie in a conoidal surface and the apices of both said conoidal surfaces lie at the same end of the turbine.
  • the rotor is formed as a cylindrical body e from which project radially the rows of blades 1 and the tips of these blades lie in a somewhat conical surface or surfaces the larger diameter of which is at the end of the rotor adjacent to the collar and the smaller diameter of which is at the middle of the length of the rotor.
  • the associated half 9 of the encircling stator is correspondingly coned or tapered.
  • the rotor is formed as a conoidal body h from which project radially the rows of blades 2' and the tips of these blades lie in a cylindrical surface or surfaces concentric with the cylindrical internal face of the stator whilst the tips of the stator blades is lie on a conoidal surface or surfaces closely adjacent to the external surface of the conoidal body h.
  • the two conoidal surfaces are co-extensive in the arrangement shown.
  • the varying clearances i. e., those clearances which vary with relative'axial movement of rotor and stator, on the half e adjacent to the collar 1) are those between the tips of the moving blades f and the coned cylinder bore 9, and on the other half h are those between the tips of the fixed blades is and the surfaces 7' of the coned rotor.
  • relative axial movement of rotor and stator causes all the said clearances to be affected in the same way, that is, they are all diminished or all increased, with the result that they may be set to have a minimum value when the greatest axial displacement has taken place and may be arranged so that under any other conditions these clearances increase. For instance, if the rotor expands more than the stator when heated up to full power service conditions, then the thrust block faces ad will be so adjusted that the radial blade clearances are a minimum under those full power service conditions.
  • the thrust block may be set so that the radial blade clearances are at their minimum values under full power service conditions, i. e., when the temperature is at a maximum; under any lower temperature conditions these clearances wouldlincrease.
  • the diameter of the annulus m between the rotor and stator of one half of the turbine is substantially equal near the inlet region to the annulus n of the other half, but if desired these annuli may instead be made substantially equal at the outlet ends.
  • the two conoidal surfaces 9, 7' instead of being co-extensive may be of different diameters at both ends.
  • the capacities of the two flow passages may be different if desired and in cases where they are so arranged that the axial thrusts on the rotor do not balance, dummies or other balancing devices may be employed in order to relieve the axial force on the thrust block.
  • the residual thrust is such as to tend to reduce the clearances
  • the residual thrust is preferably obtained by making the appropriate section greater in capacity or in diameter or in both capacity and diameter than the other section.
  • a double flow elastic fluid turbine embodying a casing, two opposed-flow stator sections in said casing, inward projections constituting stator blades on each section, a rotor body lying in both sections, outward projections on the rotor constituting rotor blades in each section, the surface containing the tips of the rotor blades of one section being conoidal and the surface containing the stator blades of that section being.
  • cylindrical, the surface containing the rotor blades in the other section being cylindrical and the surface containing the stator blades of that section conoidal and the apices of the two said conoidal surfaces lying at the same end of the turbine.
  • a double flow elastic fluid turbine embodying a casing, two opposed-flow stator sections in said casing, inward projections constituting stator blades on each section, a rotor body lying in both sections within the tips of the said projections, outward projections on the rotor constituting rotor blades in each section, the surfaces containing the tips of the blades being in one section conoidal in the case of the rotor blades and cylindrical in the case of the stator blades and in the other section cylindrical in the case of the rotor blades and conoidal in the case of the stator blades and the apices of the two said conoidal surfaces lying at the same end of the turbine.
  • a double flow elastic fluid turbine embodying a casing, two opposed-flow stator sections in said casing, inward projections constituting stator blades on each section, a rotor body lying in both sections, outward projections on the rotor constituting rotor blades in each section, the surface containing the tips of the rotor blades of one section being conoidal and the surface containing the stator blades of that section being cylindrical, the surface containing the rotor blades in the other section being cylindrical and the surface containing the stator blades of that section conoidal, a thrust or axial-adjustment device for one end of said rotor body, the apices of both conoidal surfaces lying at the end of the turbine remote from that at which the said thrust or axial-adjustment device is disposed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US322194A 1939-03-04 1940-03-04 Elastic fluid turbine Expired - Lifetime US2276563A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2276563X 1939-03-04

Publications (1)

Publication Number Publication Date
US2276563A true US2276563A (en) 1942-03-17

Family

ID=10902843

Family Applications (1)

Application Number Title Priority Date Filing Date
US322194A Expired - Lifetime US2276563A (en) 1939-03-04 1940-03-04 Elastic fluid turbine

Country Status (3)

Country Link
US (1) US2276563A (enrdf_load_stackoverflow)
FR (1) FR862051A (enrdf_load_stackoverflow)
NL (1) NL52847C (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2525698A (en) * 1945-05-11 1950-10-10 Hazeltine Research Inc Compensated voltage regulator

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2525698A (en) * 1945-05-11 1950-10-10 Hazeltine Research Inc Compensated voltage regulator

Also Published As

Publication number Publication date
FR862051A (fr) 1941-02-26
NL52847C (enrdf_load_stackoverflow)

Similar Documents

Publication Publication Date Title
US3056579A (en) Rotor construction
US2349187A (en) Vibration dampener
US4972986A (en) Circumferential inter-seal for sealing between relatively rotatable concentric shafts
US3520635A (en) Turbomachine shroud assembly
US10428672B2 (en) Floating, non-contact seal and dimensions thereof
US2619317A (en) Rotor for turbomachines
US1651855A (en) Elastic-fluid turbine
US1505647A (en) Packing for elastic-fluid turbines and the like
JPH0112968B2 (enrdf_load_stackoverflow)
US2762559A (en) Axial flow compressor with axially adjustable rotor
US2552239A (en) Turbine rotor cooling arrangement
US2689682A (en) Gas turbine compressor
US2638743A (en) Construction of turbine-inlet and stator elements of gas turbines
US2276563A (en) Elastic fluid turbine
US2919890A (en) Adjustable gas turbine nozzle assembly
US2220616A (en) Packing for steam turbines
US2920867A (en) Reheat turbine apparatus
US1680737A (en) Elastic-fluid turbine
US3544233A (en) Turbine nozzle chamber support arrangement
US4135849A (en) Pinned root turbine blade providing maximum friction damping
US2047501A (en) Steam or gas turbine
US2426461A (en) Gland packing
US2102637A (en) Arrangement of radially traversed blades in rotary machines
US2540902A (en) Thrust balancing means
RU2005890C1 (ru) Ступень турбомашины б.и.стрикицы