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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Применить Всего найдено 7. Отображено 7.
11-04-2013 дата публикации

ROTOR DISC AND METHOD OF BALANCING

Номер: US20130086805A1
Автор: LECUYER Joseph Daniel, PRONOVOST Christian
Принадлежит: PRATT & WHITNEY CANADA CORP.

A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life. 1. A method of manufacturing a turbomachine rotor disc , the method comprising:providing the turbomachine rotor disc with at least one generally annular appendage coaxially disposed with reference to a central rotation axis of the turbomachine rotor disc; andmachining a plurality of spaced-apart and substantially radially-extending slots in a free end of the appendage, the slots delimiting a plurality of sacrificial protrusions from which material can be removed during balancing.2. The method as defined in claim 1 , wherein the spaced-apart slots are circumferentially equally spaced on the free end of the appendage.3. The method as defined in claim 1 , wherein the turbomachine rotor disc comprises a plurality of blade receiving slots on an outer periphery thereof.4. A method for gas turbine rotor disc balancing comprising the steps of:providing a rotor disc having at least one balancing assembly provided substantially coaxially with reference a rotation axis of the rotor disc, the balancing assembly having a plurality of spaced-apart sacrificial protrusions extending between adjacent stress-relieving slots, bottoms of said adjacent slots defining a base end of the protrusions, each protrusion extending from its base end to a free end, the slots provided with a shape providing a stress concentration below a crack propagation threshold in a region of the slot bottoms;determining an imbalance to the rotor disc; and thenremedying the imbalance by ...

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Номер записи: 1
02-05-2013 дата публикации

ROTOR BLADE ASSEMBLY TOOL FOR GAS TURBINE ENGINE

Номер: US20130104398A1
Автор: CHATELOIS Bruno, LECUYER Joseph Daniel
Принадлежит:

A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure 1. A rotor blade assembly tool or coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor , wherein each rotor blade extends from the rotor disc to a radially outer blade tip and includes a platform extending from the rotor blade in opposed circumferential directions , a plurality of components are each disposed radially between the respective platforms of the rotor blades and the disc , and circumferentially between adjacent said rotor blades , the tool comprising:a base ring; andan array of circumferentially spaced resilient fingers supported on the base ring, the fingers extending in a substantially axial direction and being configured to radially abut the components against a radially inner facing surface of the platforms, respectively, when the rotor blades are installed on the rotor disc, each of the fingers having a maximum thickness in a radial direction with respect to the rotor blade assembly, smaller than a radial clearance between the disc and a land of the respective platforms.2. The tool as defined in wherein the base ring comprises an engaging end for engaging respective rotor blades.3. The tool as defined in wherein each of the fingers comprises a curved spring band extending axially and radially outwardly from the base ring.4. The tool as defined in wherein each of the fingers is configured for resilient deformation to allow the finger to be withdrawn from the turbine rotor through the radial clearance ...

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Номер записи: 2
16-10-2014 дата публикации

ROTOR BLADE ASSEMBLY TOOL FOR GAS TURBINE ENGINE

Номер: US20140304989A1
Автор: CHATELOIS Bruno, LECUYER Joseph Daniel
Принадлежит: PRATT & WHITNEY CANADA CORP.

A rotor blade assembly tool for coupling a plurality of circumferentially spaced rotor blades to a rotor disc of a turbine rotor assembly, includes a base ring with an array of circumferentially spaced resilient fingers axially extending from the base ring. The resilient fingers are configured each to radially abut a blade seal, damper or other engine component against radially inner facing surfaces of platforms of the respective blades when the blades are being seated onto the disc during an assembly procedure 1. A method of assembling a rotor assembly for a gas turbine engine , the method comprising:providing a plurality of rotor blades each including a root and a platform, the platform extending from the blade in opposed circumferential directions;providing a rotor disc including a plurality of slots spaced circumferentially about the disc;providing a plurality of blade seal members for sealing circumferential gaps between adjacent said platforms when the rotor blades are installed on the rotor disc;partially inserting the roots of the rotor blades in the respective slots of the rotor disc;placing the respective seal members radially between the platforms and the rotor disc, each seal member being positioned circumferentially between adjacent said rotor blades using a tool having an array of circumferentially spaced resilient fingers radially abutting the respective seal members against radially inner facing surfaces of the platforms;seating the rotor blades in the respective slots of the rotor disc substantially simultaneously with attachment of the respective seal members to the platforms, by a relative movement between the rotor disc and the tool having the rotor blades with the attached seal members, thereby forming the rotor assembly; and thenmoving the tool away from the rotor assembly to withdraw the respective resilient fingers from a radial clearance between the rotor disc and respective lands of the platforms with the blade seal members remaining in ...

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Номер записи: 3
16-04-2013 дата публикации

Rotor disc and method of balancing

Номер: CA2672837C
Автор: Christian Pronovost, Joseph Daniel Lecuyer
Принадлежит: Pratt and Whitney Canada Corp

A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life.

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Номер записи: 4
19-02-2011 дата публикации

Balancing apparatus for rotor assembly

Номер: CA2712143A1
Автор: Bruno Chatelois, Joseph Daniel Lecuyer
Принадлежит: Pratt and Whitney Canada Corp

A balancing assembly for a rotor assembly of a gas turbine engine includes a flange engaging portion defining a flange receiving opening for mating with the flange in a slidable manner. A hole extends through at least part of the flange engaging portion, the hole corresponding in size to a recess and adapted to receive a rivet or other suitable fastener to fix the balancing weight with respect to the disc.

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Номер записи: 5
30-03-2010 дата публикации

Rotor disc and method of balancing

Номер: CA2672837A1
Автор: Christian Pronovost, Joseph Daniel Lecuyer
Принадлежит: Pratt and Whitney Canada Corp

A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life.

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Номер записи: 6
20-11-2012 дата публикации

Balancing apparatus for rotor assembly

Номер: CA2712143C
Автор: Bruno Chatelois, Joseph Daniel Lecuyer
Принадлежит: Pratt and Whitney Canada Corp

A balancing assembly for a rotor assembly of a gas turbine engine includes a flange engaging portion defining a flange receiving opening for mating with the flange in a slidable manner. A hole extends through at least part of the flange engaging portion, the hole corresponding in size to a recess and adapted to receive a rivet or other suitable fastener to fix the balancing weight with respect to the disc.

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Номер записи: 7