Rotor blade assembly comprising a ring segment shaped or disc segment shaped blade carrier and a radially inner reinforcement structure

Patent metadata

Field	Value
Publication number	US-10794199-B2
Application number	US-201715729793-A
Country	US
Kind code	B2
Filing date	Oct 11, 2017
Priority date	Oct 12, 2016
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.

First claim

The invention claimed is:

1. A rotor blade assembly group for an engine, comprising:
a blade carrier including a plurality of rotor blades that are provided along a first circle line about a central axis of the rotor blade assembly group,
the blade carrier including a carrier section that extends radially inward in a direction toward the central axis with respect to the plurality of rotor blades,
the carrier section comprising a connection area positioned at a radially innermost portion of the carrier section farthest from the plurality of rotor blades,
at least one stiffening ring fixedly attached at the connection area of the carrier section,
the at least one stiffening ring being arranged at a first or a second face side of the blade carrier,
the blade carrier being formed in a ring-segment-shaped or a disc-segment-shaped manner,
the connection area of the carrier section including a profile that includes at least one axial projection, with the profile having a T-shaped, I-shaped, or fir tree shaped cross-section, the at least one stiffening ring engaging around the profile in a form-fit manner, such that the at least one axial projection is received at least partially between a radially outer section and a radially inner section of the at least one stiffening ring, and
a sleeve-shaped connection component for connecting the blade carrier to at least one other adjacent blade carrier via a bolt connection element, and such that the bolt connection element connects the sleeve-shaped connection component and an extension of the at least one stiffening ring to the blade carrier,
wherein the blade carrier includes a passage hole that extends axially with respect to the central axis and that is radially delimited by a radially innermost edge of the carrier section, and a portion of the radially inner section of the at least one stiffening ring axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section.

2. The rotor blade assembly group according to claim 1 , wherein:
the at least one stiffening ring includes a first stiffening ring and a second stiffening ring, the first stiffening ring and the second stiffening ring fixedly attached at the connection area of the carrier section,
the first stiffening ring is arranged at the first face side of the blade carrier and the second stiffening ring is arranged at the second face side of the blade carrier, such that the second face side is facing away from the first face side, and
the first and second stiffening rings are connected to the connection area of the carrier section and in addition are connected to each other.

3. The rotor blade assembly group according to claim 2 , wherein at least one of the first stiffening ring and the second stiffening ring is made of a metal matrix composite.

4. The rotor blade assembly group according to claim 2 , wherein at least one of the first stiffening ring and the second stiffening ring includes an internal core made of a metal matrix composite.

5. The rotor blade assembly group according to claim 4 , wherein the at least one stiffening ring that includes the internal core made of the metal matrix composite is configured such that the internal core made of the metal matrix composite axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section.

6. The rotor blade assembly group according to claim 1 , wherein the profile of the connection area of the carrier section that has the T-shaped, I-shaped, or fir tree shaped cross-section extends along a second circle line about the central axis of the rotor blade assembly group at least in certain sections.

7. A gas turbine engine with at least one rotor blade assembly group according to claim 5 .

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Gaebler Miklos
• Brueggmann Sven

Classifications

• F01D5/3038

  the slot having inwardly directed abutment faces on both sides · CPC title

• F01D5/022 Primary

  with concentric rows of axial blades · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title

• F01D5/066

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F01D5/3007

  of axial insertion type · CPC title