Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.


  1. Advanced Patent Search
Publication numberUS899319 A
Publication typeGrant
Publication dateSep 22, 1908
Filing dateOct 8, 1906
Priority dateOct 8, 1906
Publication numberUS 899319 A, US 899319A, US-A-899319, US899319 A, US899319A
InventorsGeorge Gerald Stoney
Original AssigneeCharles Algernon Parsons
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
US 899319 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)



. APPLIOATION FILED 0012's. 1006.

Patented Sept. 22, 1908.




Specification of Letters Patent.

Patented Sept. 22, 1908. 1

Application filed Octobera, 1906. Serial No. 337,966.

ings and especially to the fluid packings of blades. I In order to reduce the clearance necessary in turbines and to reduce the chances of damage by contact due to distortion, strips with their edges projecting towards the o posing member have been secured to t e blades, these edges being adapted to wear when contact takes place.

The objects of the present invention are to provide means to (1) reduce the tendency ofturbine or compressorblades to damage them-: selves or the casing orspindle or to stri ping of blades taking place on account of too c osecontact between the blade ends and the cylinder or drum especially where tightness is secured by small clearances between the blade tips or bladeshrouding and the cylinder or drum, and (2) reduce the skin friction between the blade ends or shrouding of the blades and the surface of the cylinderor drum which in the case of steam turbines may be caused by the presence of water from the steam. or from water of "condensation lying between the fixed and moving surfaces of small clearance. The invention consists in forming the ends of the blades with narrow edges or in pro-- viding on the blades or the casing or drum, strips of serrated cross section so that if too close contact takes place between a fixed and a moving part very. narrow edges only are subjected to the wearing action whereby the tendency to damage or stripping and the losses due to skin friction are reduced.

According to onemethod of carrying the invention into effect, the end of the'bladeis sharpened or brought to a thin edge by grinding, milling, filing, stam ing, taperdrawing or other means. The b ade may be chamfered off .on the concave or convex sides and the 'chamfer may be straight or curved, preferably a concave curve so as to allow, if desired, a greater amount of wear before the thick part of the blade is reached, the thin edge being thereby better preserved. By this method greater security against damage to the blade is obtained should the cylinder or shaft become distorted or the bearings of the shaft Wear or become out of line with the bore; and also the area of blade and surface moving at high velocity and in close proximity relative to the cylinder or drum is much reduced and the skin friction from water thereby reduced.

According to another method of carrying the invention into effect, serrations are rovided on a brass orthe like shrouding o the blade member or on a separate brass or the like striplfixed on the cylinder or drum 0' posite to t I serrations consisting of thin metal edges of small thickness compared with their pitch.

These serrations preferably lie in the circumferential direction-but maybe oblique. like a screw, the obliquity being referably such' a direction as to assist t e flow away of,

The projections may {80.

water to, the exhaust. also be continuous or more or'less discontinuous. They may be formed on the blade shroudin before or after attachment to the blades. en attached to the cylinder or drum the strips carrying the thin metal serrations or edges are inserted separately in giooves and calked or otherwise removably ed' therein. I

- Referring now to the accompanyinfg Figure 1 is a horizontal section through aturbine blade, Fig. 2 rergesents six modified sections on the line A of Fig: 1. Fig. 3 is a detail sectional view of a turbine spindle and in which a serrated strip of brass or Accordin to the forms of section shown in Fig. 2 the b ade is'in, or, shown thinned at the end by fullering out on both sides; in b, thinned by fullerin on one side only, while the form 0, shows t e fullering on the opposite side. In the case of d, the thinning 210- cording to this invention is effected by making an inclined edge on. both the concave and convex sides.

e blade ends,- the projections o the draw I 'ings which form part of this speci cation. 90

' next.

" fixed on the turbine drum or spindle.

' ters Patent is:

' convex form on either side of the blade and that many other forms. of thinning may be adopted. I T

In Fig. 3, the moving blades, 9 are secured in the turbine spindle, j, in any well known manner, as for instance by insertin them in grooves in the carrier and then ca ing in a distance iece, s, between each blade and the T e' fixed blades, h, are-similarly see cured to the casing,7c. Opposite the blades, 9, there are. rovided serrated strips, m, of brassv or the like, fixed in the casing,.while opposite the blades, h, 'a serrated strip, p,'his '1 e strip, p, may be of the same form as the strip, m, in the casing or it may be made wider and be held in position by calkingthe distance piece, s, over it. When these strips are worn out they may be readily replaced.

- Fig. 4 shows a form in which the blade shrouds 'n, are serrated as well as the strip pieces, p and m.

This invention is applicable to turbines and rotary com ressors working with steam,

air, gas or any uid.

Having thus described our invention what we claim as new and desire to secure'by Let- 1. A turbo-machine blade of decreasing commencing a short distance, from said end.

2. A turbo-machine blade thinned onlyiat the end remote from the member which carries it.

3. A turbo-machine blade thinned toan edge at the end only which comes opposite to the drum or casing.

4. A turbo-machine blade chamfered at the end remote from the member-which carries the blade. 1

5. Aturbo-machine blade chamfered on one side to form an edge at the end remote from the memberwhich carries the blade.

6] A turbo-machine blade chamfered on both sides-to form an edge at the end remote from the member which carries .the blade.

7. In a turbo-machine, a packing strip having a finely serrated surface. v

8. In a turbo-machine, a packing strip being reduced in cross section. I

10. A turbo machine blade of uniform width throughout its length but of reduced CHARLES ALGERNON PARSONS. GEORGE GERALD savoury.

Witnesses: V


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2459850 *Dec 10, 1945Jan 25, 1949Westinghouse Electric CorpTurbine apparatus
US2507079 *Jun 19, 1946May 9, 1950Zimmerman Charles HAbrading mechanism
US2963307 *Dec 28, 1954Dec 6, 1960Gen ElectricHoneycomb seal
US3039737 *Apr 13, 1959Jun 19, 1962Int Harvester CoDevice for controlling clearance between rotor and shroud of a turbine
US3042365 *Nov 8, 1957Jul 3, 1962Gen Motors CorpBlade shrouding
US3053694 *Feb 20, 1961Sep 11, 1962Gen ElectricAbradable material
US3068016 *Mar 31, 1958Dec 11, 1962Gen Motors CorpHigh temperature seal
US3092306 *Jan 27, 1961Jun 4, 1963Gen Motors CorpAbradable protective coating for compressor casings
US3294315 *Sep 28, 1964Dec 27, 1966Buffalo Forge CoFan construction
US4274806 *Jun 18, 1979Jun 23, 1981General Electric CompanyStaircase blade tip
US5088742 *Mar 11, 1991Feb 18, 1992Rolls-Royce PlcHydraulic seal and method of assembly
US5143383 *Feb 21, 1990Sep 1, 1992General Electric CompanyStepped tooth rotating labyrinth seal
US6457719Aug 14, 2000Oct 1, 2002United Technologies CorporationBrush seal
US7001145 *Nov 20, 2003Feb 21, 2006General Electric CompanySeal assembly for turbine, bucket/turbine including same, method for sealing interface between rotating and stationary components of a turbine
US7972109 *Jul 5, 2011General Electric CompanyMethods and apparatus for fabricating a fan assembly for use with turbine engines
US8366400 *Nov 23, 2007Feb 5, 2013Ihi CorporationCompressor rotor
US8888446 *Oct 7, 2011Nov 18, 2014General Electric CompanyTurbomachine rotor having patterned coating
US9039358 *Jan 3, 2007May 26, 2015United Technologies CorporationReplaceable blade outer air seal design
US9181814 *Nov 24, 2010Nov 10, 2015United Technology CorporationTurbine engine compressor stator
US9388701 *Jan 31, 2011Jul 12, 2016Mitsubishi Hitachi Power Systems, Ltd.Turbine
US9399918Aug 8, 2013Jul 26, 2016Mtu Aero Engines GmbhBlade for a continuous-flow machine and a continuous-flow machine
US20050111967 *Nov 20, 2003May 26, 2005General Electric CompanySeal assembly for turbine, bucket/turbine including same, method for sealing interface between rotating and stationary components of a turbine
US20060228209 *Apr 12, 2005Oct 12, 2006General Electric CompanyAbradable seal between a turbine rotor and a stationary component
US20070077149 *Sep 22, 2006Apr 5, 2007SnecmaCompressor blade with a chamfered tip
US20070092378 *Jun 5, 2006Apr 26, 2007Rolls-Royce PlcBlade and a rotor arrangement
US20080159850 *Jan 3, 2007Jul 3, 2008United Technologies CorporationReplaceable blade outer air seal design
US20080159854 *Dec 28, 2006Jul 3, 2008General Electric CompanyMethods and apparatus for fabricating a fan assembly for use with turbine engines
US20080226460 *Nov 23, 2007Sep 18, 2008Ihi CorporationCompressor rotor
US20090072487 *Sep 18, 2007Mar 19, 2009Honeywell International, Inc.Notched tooth labyrinth seals and methods of manufacture
US20120128497 *May 24, 2012Rowley Hope CTurbine engine compressor stator
US20120269636 *Oct 25, 2012Honeywell International Inc.Blade features for turbocharger wheel
US20120288360 *Jan 31, 2011Nov 15, 2012Mitsubishi Heavy Industries, Ltd.Turbine
US20130089412 *Oct 7, 2011Apr 11, 2013General Electric CompanyTurbomachine rotor having patterned coating
EP1529962A2 *Oct 27, 2004May 11, 2005Alstom Technology LtdCompressor rotor blade
EP1770244A1 *Sep 21, 2006Apr 4, 2007SnecmaCompressor blade with chanferred tip
EP2514922A2 *Apr 13, 2012Oct 24, 2012General Electric CompanyCompressor with blade tip geometry for reducing tip stresses
EP2696031A1 *Aug 9, 2012Feb 12, 2014MTU Aero Engines GmbHBlade for a flow machine engine and corresponding flow machine engine.
WO2014005678A1 *Jun 25, 2013Jan 9, 2014Ihi Charging Systems International GmbhTurbine and corresponding exhaust gas turbocharger
Cooperative ClassificationF01D11/08