GB776618A - Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors - Google Patents
Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressorsInfo
- Publication number
- GB776618A GB776618A GB31793/54A GB3179354A GB776618A GB 776618 A GB776618 A GB 776618A GB 31793/54 A GB31793/54 A GB 31793/54A GB 3179354 A GB3179354 A GB 3179354A GB 776618 A GB776618 A GB 776618A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- rotor
- groove
- root
- pair
- 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
Links
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
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)
Abstract
776,618. Bladed turbine and compressor rotors. ENGLISH ELECTRIC CO., Ltd. Oct. 27, 1955 [Nov. 3, 1954], No. 31793/54. Addition to 751,740. Class 110 (3). The parent Specification relates to a rotor of an axial-flow turbine or compressor in which the blades are mounted by their roots in an undercut circumferential groove, a window or recess being provided at one point in the groove to permit the blades to be pulled outwardly after entry and then moved circumferentially into position. The present invention provides alternative means to that shown in the parent Specification to prevent the final or locking blade which is disposed at the window or opening from moving radially inwards. In Figs. 1a and 1b two cheese-headed screws 15 are screwed into the root 8 of the locking blade, the heads of the screws overlying parts of the roots 7, 7<SP>1</SP> of the two adjacent blades and engaging in recesses therein. In a second embodiment, a pair of wedge members slide in an axial groove in the rotor between two blade rows, the wedges being forced apart by means of a conicallyended screw so as to engage under the narrow margins on the platforms of the two locking blades, one in each blade row. In Figs. 3a and 3b a pair of pin members 17, 17<SP>1</SP> engage in an axial slot formed in the root 8 of the locking blade, the pins being separated by a compression spring 19. When moved outwardly to the working position, the pins snap into engagement with recesses 18, 18<SP>1</SP> formed in the sides of the circumferential groove in the rotor thus preventing the blade from dropping inwardly. In a further embodiment, grooves are formed in the rotor on each side of the locking blade, a pair of obliquely cut filler pieces being inserted in each groove, each pair being secured in position by a weld seam. In Fig. 5a a screw 24 is screwed into the root 8 of the locking blade, the screw abutting against the bottom of the recess 1 which is disposed beneath the rotor groove, the projections on the blade root thereby being held in abutment with the peripheral ledges on the rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB31793/54A GB776618A (en) | 1954-11-03 | 1954-11-03 | Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB31793/54A GB776618A (en) | 1954-11-03 | 1954-11-03 | Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB776618A true GB776618A (en) | 1957-06-12 |
Family
ID=10328490
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB31793/54A Expired GB776618A (en) | 1954-11-03 | 1954-11-03 | Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB776618A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3042368A (en) * | 1960-06-29 | 1962-07-03 | Worthington Corp | Removable lock for blade wheel assembly |
| US3088708A (en) * | 1961-12-29 | 1963-05-07 | Seymour J Feinberg | Compressor blade locking device |
| DE1150689B (en) * | 1959-07-10 | 1963-06-27 | Siemens Ag | Blade lock for a rotor blade ring |
| US3807895A (en) * | 1971-11-26 | 1974-04-30 | Rolls Royce | Gas turbine engine compressors |
| EP2204541A1 (en) | 2008-12-24 | 2010-07-07 | Techspace Aero S.A. | Rotor stage of an integral bladed compressor drum of an axial turbomachine and corresponding manufacturing method. |
| US20170146020A1 (en) * | 2015-11-19 | 2017-05-25 | General Electric Company | Rotor assembly for use in a turbofan engine and method of assembling |
| CN108895030A (en) * | 2018-08-06 | 2018-11-27 | 无锡市海星船舶动力有限公司 | The compressor impeller of blade detachable type |
-
1954
- 1954-11-03 GB GB31793/54A patent/GB776618A/en not_active Expired
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1150689B (en) * | 1959-07-10 | 1963-06-27 | Siemens Ag | Blade lock for a rotor blade ring |
| US3042368A (en) * | 1960-06-29 | 1962-07-03 | Worthington Corp | Removable lock for blade wheel assembly |
| US3088708A (en) * | 1961-12-29 | 1963-05-07 | Seymour J Feinberg | Compressor blade locking device |
| US3807895A (en) * | 1971-11-26 | 1974-04-30 | Rolls Royce | Gas turbine engine compressors |
| EP2204541A1 (en) | 2008-12-24 | 2010-07-07 | Techspace Aero S.A. | Rotor stage of an integral bladed compressor drum of an axial turbomachine and corresponding manufacturing method. |
| US8414256B2 (en) | 2008-12-24 | 2013-04-09 | Techspace Aero, S.A. | One-piece bladed drum of an axial turbomachine compressor |
| US20170146020A1 (en) * | 2015-11-19 | 2017-05-25 | General Electric Company | Rotor assembly for use in a turbofan engine and method of assembling |
| US10125619B2 (en) * | 2015-11-19 | 2018-11-13 | General Electric Company | Rotor assembly for use in a turbofan engine and method of assembling |
| CN108895030A (en) * | 2018-08-06 | 2018-11-27 | 无锡市海星船舶动力有限公司 | The compressor impeller of blade detachable type |
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