Support member and a component supported thereby
AssigneeROLLS-ROYCE plc
InventorsTerence R. Pellow, Derek A. Glew
Life of this patent
Estimating the term…
Abstract
A turbine suitable for a gas turbine engine is provided with a stage of rotary aerofoil blades which is surrounded by a shroud ring made of silicon nitride. In order to minimize load transfer between the shroud ring and the turbine casing the shroud ring is radially supported by and radially spaced apart from the turbine casing by an annular brush seal.
Claims14
A structure comprising;
- an annular support member;
- an annular component, said annular support membersurrounding said annular component, and said annular component being continuous and being capable of floating radially relative to said support member;
- and
- sealing means resiliently supporting said annular component from said support member in spaced relationship therewith while permitting said annular component to have independent floating radial movement relative to said annular support member without any significant load transfer therebetween, said sealing means including an array of upstanding resilient filaments having fixed ends and free ends, said fixed ends of said array of upstanding resilient filaments being fixed to one of said annular support member and said annular component and the free ends of said annular array of filaments engaging the other of said annular support member and said annular component, said array of upstanding resilient filaments defining a brush seal between said annular support member and said annular component.
A turbine suitable for a gas turbine engine comprising:
- an annular gas passage having a radially outer wall;
- a turbine casing having a first wall portion thereof defining a portion of said radially outer wall of said gas passage and another wall portion spaced radially outwardly of said first wall portion;
- a stage of rotary aerofoil blades positioned within said annular gas passage and having an axis of rotation;
- a shroud ring positioned radially inwardly of said another wall portion of said turbine casing and surrounding and spaced from said aerofoil blades, said shroud ring being continuous and being capable of floating radially with respect to the axis of rotation and defining another portion of the radially outer wall of said annular gas passage and having at least a portion thereof made of a ceramic material, and said shroud ring and said another wall portion of said turbine casing spaced radially outwardly thereof defining an annular chamber having a radially outer wall and a radially inner wall;
- and
- sealing means resiliently supporting said shroud ring in radially spaced apart relationship from said another wall portion of said turbine casing while permitting independent floating radial movement relative to said turbine casing, said sealing means including an annular array of upstanding resilient filaments mounted on said another wall portion of said turbine casing and having free ends engaging said shroud ring, said annular array of upstanding filaments defining an annular brush seal between said trubine casing and said shroud ring and supporting said shroud ring for floating radial movement with respect to said axis of rotation without any significant load transfer between said shroud ring and said another wall portion of said turbine casing.
A turbine suitable for a gas turbine engine as claimed in claim, 13 wherein said further ceramic material is so adapted that insulating air gaps are defined between said further ceramic material and each of said silicon nitride portion and said ring-shaped support member.
Dependencies are inferred from the claim text.