IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0989552
(2006-07-19)
|
등록번호 |
US-8128374
(2012-03-06)
|
우선권정보 |
DE-10 2005 035 901 (2005-07-30) |
국제출원번호 |
PCT/DE2006/001246
(2006-07-19)
|
§371/§102 date |
20080128
(20080128)
|
국제공개번호 |
WO2007/014543
(2007-02-08)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Davidson, Davidson & Kappel, LLC
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
3 |
초록
▼
A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed betw
A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another.
대표청구항
▼
1. A securing element for securing rotor blades in position in grooves of a rotor base body of a turbine engine rotor, the grooves extending at least predominantly in the axial direction, the securing element comprising: a plate-shaped base member, the base member having an approximately centrally d
1. A securing element for securing rotor blades in position in grooves of a rotor base body of a turbine engine rotor, the grooves extending at least predominantly in the axial direction, the securing element comprising: a plate-shaped base member, the base member having an approximately centrally disposed recess formed between two end sections of the base member so as to define a middle section of the base member extending between the two end sections, the two end sections having mutually in parallel extending bearing surfaces, wherein the middle section is dimensioned in such a way that, for the assembly operation, a ram-type tool is capable of acting exclusively on the securing element in the middle section at a distance from the two end sections thereof, thereby plastically deforming the middle section in regions where edge sections of the tool rest; anda projection formed in the region of an end section of the base member and, once the assembly operation has taken place, is disposed radially inwardly, and the projection determining a center-of-mass of the securing element in such a way that centrifugal forces acting during operation of the turbine engine rotor press the projection against a sealing surface. 2. The securing element as recited in claim 1 wherein, following assembly, the mutually in parallel extending bearing surfaces of the end sections face the rotor base body. 3. The securing element as recited in claim 1 wherein, prior to assembly, the middle section is approximately flat or uncambered, and, following assembly, the middle section has a cambered portion. 4. A method for mounting a securing element on a turbine engine rotor, for securing rotor blades in position in grooves of a rotor base body of the turbine engine rotor that extend at least predominantly in the axial direction, the method comprising: fitting, in response to plastic and elastic deformation, the securing element of claim 1 into annular grooves of the rotor base body and of the rotor blades between two circumferentially spaced apart locking elements, by snapping in place or engagingly fitting end sections of the securing element into the annular grooves;using a ram-shaped tool to overbend the middle section of the plate shaped base member to a predetermined degree, wherein the ram-type tool is pressed against the securing element exclusively in the middle section at a distance from the two end sections thereof, thereby plastically deforming the middle section in regions against which edge sections of the tool rest; andin a rebounding process, the securing element being subsequently straightened out and, when the ram-type tool is removed, the ends sections coming to rest engagingly in the annular grooves in a predetermined manner. 5. The method as recited in claim 4, wherein, following removal of the tool, the two end sections of the securing element extend approximately mutually in parallel, respectively in alignment. 6. The method as recited in claim 4 wherein following removal of the tool, the middle section has a cambered portion. 7. A rotor of a turbine engine comprising: a rotor base body, the rotor base body having a plurality of axial grooves extending at least predominantly in the axial direction or in a direction of flow;a plurality of rotor blades, each rotor blade being anchored via a blade root in an axial groove of the rotor base body, and, before being axially displaced, the rotor blades being secured in their anchoring position in the rotor base body by securing elements and locking elements guided in annular grooves of the rotor base body and of the rotor blades;the securing elements as recited in claim 1 being positioned in the annular grooves. 8. The rotor as recited in claim 7 wherein the rotor is a gas turbine rotor.
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