GB2026101A - Rotor blade fixing - Google Patents

Rotor blade fixing Download PDF

Info

Publication number
GB2026101A
GB2026101A GB7922107A GB7922107A GB2026101A GB 2026101 A GB2026101 A GB 2026101A GB 7922107 A GB7922107 A GB 7922107A GB 7922107 A GB7922107 A GB 7922107A GB 2026101 A GB2026101 A GB 2026101A
Authority
GB
United Kingdom
Prior art keywords
blade
plate
rotor
locking device
tabs
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.)
Withdrawn
Application number
GB7922107A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB7922107A priority Critical patent/GB2026101A/en
Publication of GB2026101A publication Critical patent/GB2026101A/en
Withdrawn legal-status Critical Current

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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor

Abstract

A lockplate for a gas turbine engine rotor blade comprises a first piece which is permanently retained on the rotor 12 by tabs 18a and also has a tab 18b which in use abuts one flank of the blade root 14 and a second piece which has a tongue removably engageable with a slot in the first piece and a tab 20a which in use abuts the opposite flank of the blade root to that abutted by the tab on the first piece. The first part therefore remains in situ when a blade is removed, and only the second part need be discarded. <IMAGE>

Description

SPECIFICATION A blade locking device The invention relates to blade locking devices more particularly for use in retaining the blades of gas turbine engine to their rotors.
The rotating blades of gas turbine engines can be retained on their rotors by a number of locking devices, one of which consists of a lockplate which is inserted between the base of the blade and its associated rotor. The lockplate has tabs which are bent to secure the lockplate to the rotor and the blade to the lockplate and therefore the rotor.
When a blade which is fitted with such a lockplate has to be removed from the rotor, the tabs are bent back to their original position, the lockplate is removed and the blade withdrawn from the rotor. The lockplate is discarded because once the tabs have been bent it cannot be used again.
The present invention seeks to provide a blade locking device, a part of which remains in situ when a blade is removed and only a part of which has to be discarded.
According to the present invention there is provided a blade locking device suitable for use in retaining a blade of a fluid flow machine to a rotor, the locking means comprising a first plate which is securable to a rotor and having means for partially retaining a blade to the rotor, a second plate which is removably attached to the first plate and also having means for partially retaining the blade to the rotor, the partial retaining means of the first and second plates providing a complete retaining means for the blade.
The first plate may be secured to the rotor by tabs at each end of the plate, and the partial retaining means on the first plate may comprise a tab which in use abuts the flank of the blade root.
The second plate may be removably attached to the first plate by a tongue which engages a slot in the first plate and the partial retaining means on the second plate may be a tab which in use abuts the opposite flank of the blade root abutted by the partial retaining means of the first plate.
The present invention will now be more particularly described with reference to the accompanying drawings in which: Figure 1 shows a section through one form of blade locking device according to the present invention in situ.
Figure 2 is a plan view of the first plate of the locking device shown in Fig. 1 and, Figure 3 is a plane view of the second plate of the locking device shown in Fig. 1.
Referring to the Figures, a blade locking device 10 is shown in situ between a rotor 1 2 of a gas turbine engine (not shown) and a blade 14 only a part of which is shown. Two silicone rubber pads 1 6 are positioned between the locking device 10 and the rotor 1 2.
The locking device 10 comprises a first plate 1 8 and a second plate 20 which is removably attached (Fig. 1) to the first plate by a tongue 22 (Fig. 3) which engages a slot 24 (Fig. 2) in the first plate. The first plate 18 has two tabs 1 8a which secure the plate to the rotor and two tabs 186 which abuts the blade and partially retains the blade on the rotor.
The second plate 20 has a tab 20a which also abuts the blade but on the opposite side to that of the tabs 1 8b and also partially retains the blade on the rotor. The tabs 18b and 20a provide a complete retention of the blade to the locking device 10 and since the locking device is also secure to the rotor, the blade is retained on the rotor.
In use, the first plate is positioned between on the rotor in the correct position and the two tabs 1 8a are bent down to secure the first plate to the rotor. The second plate is attached to the first plate by engaging the tongue 22 in the slot 24 and the blade is attached to the rotor. The tabs 186 and 20a are bent up to abut opposite sides of the blade, in this case opposite sides of the blade platform. The blade is thus retained on the rotor by the locking device 10.
If it is desired to remove the blade from the rotor, the tab 20a is bent down, the blade removed and the plate 20 is removed from the plate 1 8 and discarded. A new plate 20 is then attached to the plate 18, the blade or a replacement blade is attached to the rotor and the tab 20a of the new second plate 20 is bent up to retain the blade on the rotor.
By this means, only a small part of the locking device needs to be discarded when blades are removed.
The invention has been described in relation to the blades of a gas turbine engine it can also be used in connection with the blades of other fuel flow machines such as steam turbines, fans and pumps.
1. A blade locking device suitable for use in retaining a blade of a fluid flow machine to a rotor, the locking means comprising a first plate which is securable to a rotor and having means for partially retaining a blade to the rotor a second plate which is removably attached to the first plate and also having means for partially retaining the blade to the rotor, the partial blade retaining means of the first and second plates provides a complete retaining means for the blade.
2. A blade locking device as claimed in claim 1 in which the first plate is securable to the rotor by at least one tab at each end of the plate.
3. A blade locking device as claimed in claim 1 in which the partial retaining means on the first plate comprises at least one tab at
**WARNING** end of DESC field may overlap start of CLMS **.

Claims (6)

**WARNING** start of CLMS field may overlap end of DESC **. SPECIFICATION A blade locking device The invention relates to blade locking devices more particularly for use in retaining the blades of gas turbine engine to their rotors. The rotating blades of gas turbine engines can be retained on their rotors by a number of locking devices, one of which consists of a lockplate which is inserted between the base of the blade and its associated rotor. The lockplate has tabs which are bent to secure the lockplate to the rotor and the blade to the lockplate and therefore the rotor. When a blade which is fitted with such a lockplate has to be removed from the rotor, the tabs are bent back to their original position, the lockplate is removed and the blade withdrawn from the rotor. The lockplate is discarded because once the tabs have been bent it cannot be used again. The present invention seeks to provide a blade locking device, a part of which remains in situ when a blade is removed and only a part of which has to be discarded. According to the present invention there is provided a blade locking device suitable for use in retaining a blade of a fluid flow machine to a rotor, the locking means comprising a first plate which is securable to a rotor and having means for partially retaining a blade to the rotor, a second plate which is removably attached to the first plate and also having means for partially retaining the blade to the rotor, the partial retaining means of the first and second plates providing a complete retaining means for the blade. The first plate may be secured to the rotor by tabs at each end of the plate, and the partial retaining means on the first plate may comprise a tab which in use abuts the flank of the blade root. The second plate may be removably attached to the first plate by a tongue which engages a slot in the first plate and the partial retaining means on the second plate may be a tab which in use abuts the opposite flank of the blade root abutted by the partial retaining means of the first plate. The present invention will now be more particularly described with reference to the accompanying drawings in which: Figure 1 shows a section through one form of blade locking device according to the present invention in situ. Figure 2 is a plan view of the first plate of the locking device shown in Fig. 1 and, Figure 3 is a plane view of the second plate of the locking device shown in Fig. 1. Referring to the Figures, a blade locking device 10 is shown in situ between a rotor 1 2 of a gas turbine engine (not shown) and a blade 14 only a part of which is shown. Two silicone rubber pads 1 6 are positioned between the locking device 10 and the rotor 1 2. The locking device 10 comprises a first plate 1 8 and a second plate 20 which is removably attached (Fig. 1) to the first plate by a tongue 22 (Fig. 3) which engages a slot 24 (Fig. 2) in the first plate. The first plate 18 has two tabs 1 8a which secure the plate to the rotor and two tabs 186 which abuts the blade and partially retains the blade on the rotor. The second plate 20 has a tab 20a which also abuts the blade but on the opposite side to that of the tabs 1 8b and also partially retains the blade on the rotor. The tabs 18b and 20a provide a complete retention of the blade to the locking device 10 and since the locking device is also secure to the rotor, the blade is retained on the rotor. In use, the first plate is positioned between on the rotor in the correct position and the two tabs 1 8a are bent down to secure the first plate to the rotor. The second plate is attached to the first plate by engaging the tongue 22 in the slot 24 and the blade is attached to the rotor. The tabs 186 and 20a are bent up to abut opposite sides of the blade, in this case opposite sides of the blade platform. The blade is thus retained on the rotor by the locking device 10. If it is desired to remove the blade from the rotor, the tab 20a is bent down, the blade removed and the plate 20 is removed from the plate 1 8 and discarded. A new plate 20 is then attached to the plate 18, the blade or a replacement blade is attached to the rotor and the tab 20a of the new second plate 20 is bent up to retain the blade on the rotor. By this means, only a small part of the locking device needs to be discarded when blades are removed. The invention has been described in relation to the blades of a gas turbine engine it can also be used in connection with the blades of other fuel flow machines such as steam turbines, fans and pumps. CLAIMS
1. A blade locking device suitable for use in retaining a blade of a fluid flow machine to a rotor, the locking means comprising a first plate which is securable to a rotor and having means for partially retaining a blade to the rotor a second plate which is removably attached to the first plate and also having means for partially retaining the blade to the rotor, the partial blade retaining means of the first and second plates provides a complete retaining means for the blade.
2. A blade locking device as claimed in claim 1 in which the first plate is securable to the rotor by at least one tab at each end of the plate.
3. A blade locking device as claimed in claim 1 in which the partial retaining means on the first plate comprises at least one tab at one end of the plate and which in use abuts the flank of the blade root.
4. A blade locking device as claimed in any one of the preceding claims in which the first plate has a slot which is engageable by a tongue on the second plate.
5. A blade locking device as claimed in claim 3 in which the partial retaining means on the second plate comprises at least one tab which in use abuts the opposite flank of the blade root abutted by the partial retaining means of the first plate.
6. A blade locking device constructed and arranged for use and operation substantially as herein described with reference to and as shown in Figs. 1 to 3 of the accompanying drawings.
GB7922107A 1978-07-22 1979-06-26 Rotor blade fixing Withdrawn GB2026101A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7922107A GB2026101A (en) 1978-07-22 1979-06-26 Rotor blade fixing

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB7830784 1978-07-22
GB7922107A GB2026101A (en) 1978-07-22 1979-06-26 Rotor blade fixing

Publications (1)

Publication Number Publication Date
GB2026101A true GB2026101A (en) 1980-01-30

Family

ID=26268304

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7922107A Withdrawn GB2026101A (en) 1978-07-22 1979-06-26 Rotor blade fixing

Country Status (1)

Country Link
GB (1) GB2026101A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2535794A1 (en) * 1982-11-08 1984-05-11 Snecma AXIAL AND RADIAL BLADE SUPPORT DEVICE
US6102664A (en) * 1995-12-14 2000-08-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blading system and method for controlling structural vibrations
WO2009100975A1 (en) * 2008-02-14 2009-08-20 Siemens Aktiengesellschaft Turbomachine rotor comprising a pretensioning device for pretensioning a guide vane

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2535794A1 (en) * 1982-11-08 1984-05-11 Snecma AXIAL AND RADIAL BLADE SUPPORT DEVICE
EP0110744A1 (en) * 1982-11-08 1984-06-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for the radial and axial fixation of fan blades
US4478554A (en) * 1982-11-08 1984-10-23 S.N.E.C.M.A. Fan blade axial and radial retention device
US6102664A (en) * 1995-12-14 2000-08-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blading system and method for controlling structural vibrations
WO2009100975A1 (en) * 2008-02-14 2009-08-20 Siemens Aktiengesellschaft Turbomachine rotor comprising a pretensioning device for pretensioning a guide vane
US8512001B2 (en) 2008-02-14 2013-08-20 Siemens Aktiengesellschaft Turbomachine rotor comprising a pretensioning device for pretensioning a rotor blade

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WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)