US2401073A - Turboblade fastening - Google Patents
Turboblade fastening Download PDFInfo
- Publication number
- US2401073A US2401073A US494776A US49477643A US2401073A US 2401073 A US2401073 A US 2401073A US 494776 A US494776 A US 494776A US 49477643 A US49477643 A US 49477643A US 2401073 A US2401073 A US 2401073A
- Authority
- US
- United States
- Prior art keywords
- groove
- ring
- blades
- blade
- 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
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
Definitions
- the invention relates to a turbomachine having blades with. wedge-shaped roots let into grooves of wedge-shaped cross-section.
- the invention consists in that the cross-section of the groove is wider than the blade root and that the space remaining between the blade and one side wall of the groove is filled by a ring. This ring may, for example, be rammed into the groove.
- the cross-section of the groove is made so much wider than the blade root that the blades can be inserted at every point of the groove without the use of a lock.
- the side surface of the blade root which lies next to the inserted ring is arranged parallel to the blade axis, and the opposite surface of the blade root which is in direct contact with one of the side walls of the groove is arranged obliquely to the blade axis.
- the inserted ring may be divided into several bars, for example into at least two layers lying one above the other in the groove.
- the bars ly-' ing topmost in the groove may be held firm by caulking the blade carrier.
- the space between blade root and groove surface filled by the in serted ring may have a slightly tapered crosssection.
- Fig. 1 shows a part of a longitudinal section through a turbomachine.
- Fig. 2 shows the cross-section and Fig. 3 the longitudinal section, along the line IIIIII of Fig. 2, of a single element of the turbomachine according to Fig. 1, both on a larger scale.
- the blades 4 (Figs. 2 and 3) of the guide blading as shown in Fig. 1 have their wedge-shaped roots 5 fitted into grooves 6 of wedge-shaped cross-section.
- the cross-section of the groove is wider than the profile of the blade root, so that between the side surfaces l I of the blades and the side wall I of the groove a space is left which is filled by an inserted ring.
- the ring is by way of example divided into three bars 8, 9 and I0 lying one above the other in the groove.
- the bar 8 is introduced and rammed in until it fits close to the side surface 1 of groove 6 and to the side surface H of blade root 5. Then the bar 9 is introduced and similarly rammed in.
- the blade carrier may at first have a projecting edge I3 so that no depression is caused by the caulking.
- the bars themselves may be divided into several sections circumferentially.
- the insertion of the blades is then facilitated in that, after the introduction of a number of blades arranged in a row for the length of one section, at least one ring section can be inserted and rammed in. In this way one section after another can be inserted until finally the blading is completed.
- the fitting of the blades described above can be adopted both for the runners and for the stationary blading of turbines or compressors and is particularly suited for the stationary blades of turbines.
- the design described in the invention can be employed for radial flow machines as well as for axial turbomachines.
- a suitable material from which the inserted rings or bars may be constructed is, for example, soft iron. It may be advantageous for the outermost ring against which the edge of the groove is caulked to be made harder than the others.
- a turbomachine comprising a blade carrier, at least one groove in the carrier for the blades, said groove having one side oblique and the opposite side parallel to the blade axis, the roots of the blades being sufficiently narrower than the groove that the roots may be inserted into the groove, said roots of the blades having one oblique face which cooperates with the oblique side of the groove to wedge the blades to the carrier and the opposite face parallel to the parallel side of the groove, ring means in the groove filling the space defined by the parallel face and side when the oblique face of the root is in engagement with the oblique side of the groove, and caulking for securing the ring means in position, said ring means being divided into at least two rings the outermost of which is harder than the other which is nearer th bottom of the groove, so that the ring near the bottom of the groove may be rammed into the groove and the outermost ring is held in position by caulking the edge of the groove against it.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
May 28, 1946. w. HUB ER TURBO BLADE FASTENING Filed July 15, 1943 v INVENTOR. WALTER H0853.
-- OM'V M L4.
r A TTORNE Y5.
Patented May 28, 1946 TURBOBLADE FASTENING Walter Huber, Winterthur, Switzerland, assignor to Sulzer Freres, Societe Anonyme, Winterthur, Switzerland Application July 15, 1943, Serial No. 494,776 In Switzerland October 23, 1942 1 Claim.
The invention relates to a turbomachine having blades with. wedge-shaped roots let into grooves of wedge-shaped cross-section. The invention consists in that the cross-section of the groove is wider than the blade root and that the space remaining between the blade and one side wall of the groove is filled by a ring. This ring may, for example, be rammed into the groove. The cross-section of the groove is made so much wider than the blade root that the blades can be inserted at every point of the groove without the use of a lock. Preferably the side surface of the blade root which lies next to the inserted ring is arranged parallel to the blade axis, and the opposite surface of the blade root which is in direct contact with one of the side walls of the groove is arranged obliquely to the blade axis.
The inserted ring may be divided into several bars, for example into at least two layers lying one above the other in the groove. The bars ly-' ing topmost in the groove may be held firm by caulking the blade carrier. The space between blade root and groove surface filled by the in serted ring may have a slightly tapered crosssection.
An example of the subject matter of the invention is represented in simplified form in the drawing.
Fig. 1 shows a part of a longitudinal section through a turbomachine.
Fig. 2 shows the cross-section and Fig. 3 the longitudinal section, along the line IIIIII of Fig. 2, of a single element of the turbomachine according to Fig. 1, both on a larger scale.
In the blade carrier I (Fig. l) of a turbine or axial compressor rows of guide blading 2 are inserted in grooves 3.
The blades 4 (Figs. 2 and 3) of the guide blading as shown in Fig. 1 have their wedge-shaped roots 5 fitted into grooves 6 of wedge-shaped cross-section. The cross-section of the groove is wider than the profile of the blade root, so that between the side surfaces l I of the blades and the side wall I of the groove a space is left which is filled by an inserted ring. The ring is by way of example divided into three bars 8, 9 and I0 lying one above the other in the groove.
First the bar 8 is introduced and rammed in until it fits close to the side surface 1 of groove 6 and to the side surface H of blade root 5. Then the bar 9 is introduced and similarly rammed in.
Finally the bar II] is inserted and is made firm by caulking the edge 12 of the blade carrier l. The blade carrier may at first have a projecting edge I3 so that no depression is caused by the caulking.
The bars themselves may be divided into several sections circumferentially. The insertion of the blades is then facilitated in that, after the introduction of a number of blades arranged in a row for the length of one section, at least one ring section can be inserted and rammed in. In this way one section after another can be inserted until finally the blading is completed.
The fitting of the blades described above can be adopted both for the runners and for the stationary blading of turbines or compressors and is particularly suited for the stationary blades of turbines. The design described in the invention can be employed for radial flow machines as well as for axial turbomachines. A suitable material from which the inserted rings or bars may be constructed is, for example, soft iron. It may be advantageous for the outermost ring against which the edge of the groove is caulked to be made harder than the others.
I claim:
A turbomachine comprising a blade carrier, at least one groove in the carrier for the blades, said groove having one side oblique and the opposite side parallel to the blade axis, the roots of the blades being sufficiently narrower than the groove that the roots may be inserted into the groove, said roots of the blades having one oblique face which cooperates with the oblique side of the groove to wedge the blades to the carrier and the opposite face parallel to the parallel side of the groove, ring means in the groove filling the space defined by the parallel face and side when the oblique face of the root is in engagement with the oblique side of the groove, and caulking for securing the ring means in position, said ring means being divided into at least two rings the outermost of which is harder than the other which is nearer th bottom of the groove, so that the ring near the bottom of the groove may be rammed into the groove and the outermost ring is held in position by caulking the edge of the groove against it.
WALTER HUBER.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH568770X | 1942-10-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2401073A true US2401073A (en) | 1946-05-28 |
Family
ID=4520774
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US494776A Expired - Lifetime US2401073A (en) | 1942-10-23 | 1943-07-15 | Turboblade fastening |
Country Status (5)
Country | Link |
---|---|
US (1) | US2401073A (en) |
CH (1) | CH230327A (en) |
FR (1) | FR898251A (en) |
GB (1) | GB568770A (en) |
NL (1) | NL62129C (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4436495A (en) * | 1981-03-02 | 1984-03-13 | Arthur D. Little, Inc. | Method of fabricating two-piece scroll members for scroll apparatus and resulting scroll members |
US5131813A (en) * | 1990-04-03 | 1992-07-21 | General Electric Company | Turbine blade outer end attachment structure |
DE4203514A1 (en) * | 1992-02-07 | 1993-08-12 | Christfried Dr Lenz | Power transmission system for vehicles - has sliding carriage, connected via rod to internally toothed frame, and movement conversion device |
-
0
- NL NL62129D patent/NL62129C/xx active
-
1942
- 1942-10-23 CH CH230327D patent/CH230327A/en unknown
-
1943
- 1943-07-15 US US494776A patent/US2401073A/en not_active Expired - Lifetime
- 1943-09-23 GB GB15605/43A patent/GB568770A/en not_active Expired
- 1943-09-23 FR FR898251D patent/FR898251A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
NL62129C (en) | |
CH230327A (en) | 1943-12-31 |
FR898251A (en) | 1945-04-18 |
GB568770A (en) | 1945-04-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3216699A (en) | Airfoil member assembly | |
US3014695A (en) | Turbine bucket retaining means | |
US4915587A (en) | Apparatus for locking side entry blades into a rotor | |
US2942842A (en) | Turbine blade lock | |
US3689177A (en) | Blade constraining structure | |
US3395891A (en) | Lock for turbomachinery blades | |
US3043562A (en) | Combination sealing and restraining member for long-shank turbo-machine buckets | |
US3377050A (en) | Shrouded rotor blades | |
US3182955A (en) | Construction of turbomachinery blade elements | |
US2867408A (en) | Axial locking of rotor blades for turbines and the like | |
US1482031A (en) | Packing for rotating bodies | |
US3047268A (en) | Blade retention device | |
US3393894A (en) | Blade assembly | |
US3397865A (en) | Bladed rotor for a fluid flow machine such as a gas turbine engine | |
US3383094A (en) | Rotor blade locking means | |
US3702222A (en) | Rotor blade structure | |
US2410588A (en) | Turbine blade and assembly thereof | |
DE102010017435B4 (en) | Blade attachment mechanism for a rotary machine and turbine engine | |
US2949278A (en) | Turbine blade retention | |
US2401073A (en) | Turboblade fastening | |
US10072508B2 (en) | Turbomachine rotor with optimised bearing surfaces | |
US2857132A (en) | Turbine wheel | |
US3198485A (en) | Turbine blade lock | |
US2225769A (en) | Turbine blade | |
US3076633A (en) | Turbine and like rotor blades |