Blade tip clearance control arrangement for a gas turbine

Claim 2

A blade tip clearance control arrangement for a gas turbine engine comprising a rotor and a stator, the rotor having at least one stage of circumferentially arranged radially extending rotor blades, the rotor blades having tips, the stator comprising a first annular control member, at least one second annular control member and a radially resilient annular support member, the first annular control member having a relatively rapid response such that it expands or contracts quickly in accordance with a temperature variation, the first annular member being formed from a material having a relatively low coefficient of thermal expansion, the first annular control member being spaced radially from the blade tips by a clearance and defining a portion of a flowpath through the gas turbine engine, the at least one second annular control member having a relatively slow response rate such that it expands or contracts slowly in accordance with a temperature variation, the second annular control member being formed from a material having a relatively high coefficient of thermal expansion, the first annular control member being arranged coaxially with and radially inwardly of the second annular control member, the radially resilient annular support member secured immovably to both the first annular control member and the second annular control member whereby the first annular control member initially expands relatively rapidly in a first phase of thermal expansion in accordance with the rate of expansion of the first annular control member against the combined resilience of the resilient annular support member and the second annular control member until the first annular control member is fully thermally expanded, the first annular control member being caused to expand relatively slowly in a second phase of thermal expansion in accordance with the rate of expansion of the second annular control member by the resilience of the resilient annular support member, the first annular control member initially contracting relatively rapidly in a first phase of thermal contraction in accordance with the rate of contraction of the first annular control member against the combined resilience of the resilient annular support member and the second annular control member, the first annular control member being caused to contract relatively slowly in a second phase of thermal contraction in accordance with the rate of contraction of the second annular control member by the resilience of the resilient annular support member.

Claim 3

The blade tip clearance control arrangement as claimed in claim 1 in which two second annular control members are axially spaced, the first annular control member is arranged coaxially with and radially inwardly of the second annular control members, the radially resilient annular support member is secured immovably to both the first annular control member and the second annular control members, the radially resilient annular support member has axial ends and a mid portion between the two axial ends, the axial ends of the resilient annular support member are secured to the second annular control members, and the first annular control member is connected to the resilient annular support member by connection means substantially at the mid portion of the resilient annular support member.

Claim 4

The blade tip clearance control arrangement as claimed in claim 2 in which the first annular control member, the resilient annular support member, and the connection means are integrally formed.

Claim 5

The blade tip clearance control arrangement as claimed in claim 2 wherein the rotor comprises a plurality of axially spaced stages of the rotor blades, and wherein the stator comprises a plurality of the first annular control members each one of which is spaced radially from the blade tips of a respective one of the stages of rotor blades by a clearance, each first annular control member being arranged coaxially with and radially inwardly of a respective pair of second annular control members, a respective resilient annular support member being arranged to interconnect each first annular control member and the respective pair of second annular control members, each radially resilient support member having axial ends and a mid portion between the two ends, the axial ends of each resilient annular support member being secured to the respective pair of second annular control members, each first annular control member being connected to the respective resilient annular support member by connection means substantially at the mid portion of the resilient annular support member.

Claim 6

The blade tip clearance control arrangement as claimed in claim 4 in which each pair of second annular control members comprises an axially upstream second annular control member and an axially downstream second annular control member, the axially upstream second annular control member of at least one pair of second annular control members is secured to the axially downstream second annular control member of the pair of second annular control members axially adjacent in an upstream direction by an annular casing member such that the second annular control members, the resilient annular members and the annular casing member define a stator casing.

Claim 7

The blade tip clearance control arrangement as claimed in claim 5 in which a stage of stator vanes is positioned axially between adjacent stages of rotor blades, each stage of stator vanes having an upstream end and a downstream end, each stage of stator vanes being secured at their upstream end and downstream end to said first annular control members.

Claim 8

The blade tip clearance control arrangement as claimed in claim 5 in which the axially upstream second annular control member of at least one pair of second annular control members, the axially downstream second annular control member of the pair of second annular control member axially adjacent in an upstream direction and the annular casing member are formed integrally.

Claim 9

The blade tip clearance control arrangement as claimed in claim 1 in which the ratio of the thermal expansion coefficient of the at least one second annular control member to the thermal expansion coefficient of the first annular control member is between 1 and 2.

Claim 10

The blade tip clearance control arrangement as claimed in claim 8 in which the ratio of the thermal expansion coefficient of the at least one second annular control member to the thermal expansion coefficient of the first annular control member is between 1.3 and 1.4.

Claim 11

The blade tip clearance control arrangement as claimed in claim 1 in which the second control member has an insulating coating.

Claim 12

The blade tip clearance control arrangement as claimed in claim 1 in which the rotor is a compressor rotor.

Claim 13

The blade tip clearance control arrangement as claimed in claim 11 in which the rotor and rotor blades are formed from titanium.

Claim 14

The blade tip clearance control arrangement as claimed in claim 12 in which the first annular control member is formed from a high temperature resistant steel, the second annular control member is formed from a nickel alloy.

Claim 15

The blade tip clearance control arrangement as claimed in claim 12 in which the first and second annular control members are formed from a high temperature resistant steel.

Claim 16

The blade tip clearance control arrangement as claimed in claim 2 in which the radially resilient annular support member is formed from a selected material and has a selected axial length and a selected thickness to control the expansion of the first annular control member.

Claim 17

The blade tip clearance control arrangement for a gas turbine engine comprising a rotor and a stator, the rotor having at least one stage of circumferentially arranged radially extending rotor blades, the rotor blades having tips, the stator comprising a first annular control member, at least one second annular control member and a radially resilient annular support member secured immovably to both said first annular control member and said at least one second control member, the first annular control member having a relatively rapid response rate such that it expands or contracts quickly in accordance with a temperature variation, the first annular member being formed from a material having a relatively low coefficient of thermal expansion, the first annular control member being spaced radially from the blade tips by a clearance and defining a portion of a flowpath through the gas turbine engine, the at least one second annular control member having a relatively slow response rate such that it expands or contracts slowly in accordance with a temperature variation, the second annular control member being formed from a material having a relatively high coefficient of thermal expansion, the first annular control member being arranged coaxially with and radially inwardly of the second annular control member, the radially resilient annular support member being arranged to interconnect the first annular control member and the second annular control member whereby the first annular control member initially expands relatively rapidly in a first phase of thermal expansion in accordance with the rate of expansion of the first annular control member against the combined resilience of the resilient annular support member and the second annular control member until the first annular control member is fully thermally expanded, the first annular control member expanding relatively slowly in a second phase of thermal expansion in accordance with the rate of expansion of the second annular control member by the resilience of the resilient annular support member, the first annular control member initially contracts relatively rapidly in a first phase of thermal contraction in accordance with the rate of contraction of the first annular control member against the combined resilience of the resilient annular support member and the second annular control member, the first annular control member contracting relatively slowly in a second phase of thermal contraction in accordance with the rate of contraction of the second annular control member by the resilience of the resilient annular support member, wherein two second annular control members are axially spaced, the first annular control member being arranged coaxially with and radially inwardly of the second annular control members, the radially resilient annular support member being arranged to interconnect the first annular control member and the second annular control members, the radially resilient annular support member having axial ends and a mid portion between the two axial ends, the axial ends of the resilient annular support member being secured to the second annular control members, the first annular control member being connected to the resilient annular support member by connection means substantially at the mid portion of the resilient annular support member, wherein the rotor comprises a plurality of axially spaced stages of the rotor blades, and wherein the stator comprises a plurality of the first annular control members each one of which is spaced radially from the blade tips of a respective one of the stages of rotor blades by a clearance, each first annular control member being arranged coaxially with and radially inwardly of a respective pair of second annular control members, a respective resilient annular support member being arranged to interconnect each first annular control member and the respective pair of second annular control members, each radially resilient support member having axial ends and a mid portion between the two ends, the axial ends of each resilient annular support member being secured to the respective pair of second annular control members, each first annular control member being connected to the respective resilient annular support member by connection means substantially at the mid portion of the resilient annular support member, wherein each pair of second annular control members comprises an axially upstream second annular control member and an axially downstream second annular control member, the axially upstream second annular control member of at least one pair of second annular control members being secured to the axially downstream second annular control member of the pair of second annular control members axially adjacent in an upstream direction by an annular casing member such that the second annular control members, the resilient annular members and the annular casing member define a stator casing, the axially upstream second annular control member of at least one pair of second annular control members, the axially downstream second annular control member of the pair of second annular control members axially adjacent in an upstream direction and the annular casing member being formed integrally.

Claim 18

The blade tip clearance control arrangement for a gas turbine engine comprising a rotor and a stator, the rotor having at least one stage of circumferentially arranged radially extending rotor blades, the rotor blades having tips, the stator comprising a first annular control member, at least one second annular control member and a radially resilient annular support member secured immovably to both said first annular control member and said at least one second control member, the first annular control member having a relatively rapid response rate such that it expands or contracts quickly in accordance with a temperature variation, the first annular member being formed from a material having a relatively low coefficient of thermal expansion, the first annular control member being spaced radially from the blade tips by a clearance and defining a portion of a flowpath through the gas turbine engine, the at least one second annular control member having a relatively slow response rate such that it expands or contracts slowly in accordance with a temperature variation, the second annular control member being formed from a material having a relatively high coefficient of thermal expansion, the first annular control member being arranged coaxially with and radially inwardly of the second annular control member, the radially resilient annular support member being arranged to interconnect the first annular control member and the second annular control member whereby the first annular control member initially expands relatively rapidly in a first phase of thermal expansion in accordance with the rate of expansion of the first annular control member against the combined resilience of the resilient annular support member and the second annular control member until the first annular control member is fully thermally expanded, the first annular control member expanding relatively slowly in a second phase of thermal expansion in accordance with the rate of expansion of the second annular control member by the resilience of the resilient annular support member, the first annular control member initially contracts relatively rapidly in a first phase of thermal contraction in accordance with the rate of contraction of the first annular control member against the combined resilience of the resilient annular support member and the second annular control member, the first annular control member contracting relatively slowly in a second phase of thermal contraction in accordance with the rate of contraction of the second annular control member by the resilience of the resilient annular support member, wherein two second annular control members are axially spaced, the first annular control member being arranged coaxially with and radially inwardly of the second annular control members, the radially resilient annular support member being arranged to interconnect the first annular control member and the second annular control members, the radially resilient annular support member having axial ends and a mid portion between the two axial ends, the axial ends of the resilient annular support member being secured to the second annular control members, the first annular control member being connected to the resilient annular support member by connection means substantially at the mid portion of the resilient annular support member, wherein the rotor comprises a plurality of axially spaced stages of the rotor blades, and wherein the stator comprises a plurality of the first annular control members each one of which is spaced radially from the blade tips of a respective one of the stages of rotor blades by a clearance, each first annular control member being arranged coaxially with and radially inwardly of a respective pair of second annular control members, a respective resilient annular support member being arranged to interconnect each first annular control member and the respective pair of second annular control members, each radially resilient support member having axial ends and a mid portion between the two ends, the axial ends of each resilient annular support member being secured to the respective pair of second annular control members, each first annular control member being connected to the respective resilient annular support member by connection means substantially at the mid portion of the resilient annular support member, wherein each pair of second annular control members comprises an axially upstream second annular control member and an axially downstream second annular control member, the axially upstream second annular control member of at least one pair of second annular control members being secured to the axially downstream second annular control member of the pair of second annular control members axially adjacent in an upstream direction by an annular casing member such that the second annular control members, the resilient annular members and the annular casing member define a stator casing, the axially upstream second annular control member of at least one pair of second annular control members, the axially downstream second annular control member of the pair of second annular control members axially adjacent in an upstream direction and the annular casing member being formed integrally.

Claim 19

A blade tip clearance control structure in a gas turbine engine of the type having a rotor mounted for rotation about an axis and a plurality of radially extending blades mounted on the rotor for rotation therewith, the clearance control structure comprising: a first annular control member having a surface extending a selected axial length confronting the blade tips and spaced therefrom to define a gas flowpath therebetween, said first annular control member fabricated from a material having a first coefficient of expansion and a first expansion-and-contraction response to temperature variation; a second annular control member radially outward of said first annular control member and fabricated from a material having a second coefficient of expansion and a second expansion-and-contraction response to temperature variation; a radially resilient annular support member resiliently interconnecting said first and second annular control members and having a portion thereof fixed integrally to said first annular control member and another portion thereof fixed integrally to said second annular control member, said first coefficient of expansion being lower than that of said second coefficient of expansion and said first expansion-and-contraction response to temperature being more rapid than said second expansion-and-contraction response.

Claim 20

A blade tip clearance control structure in a gas turbine engine of the type having a rotor mounted for rotation about an axis and a plurality of radially extending blades mounted on the rotor for rotation therewith, the clearance control structure comprising: a first annular control member having a surface extending a selected axial length confronting the blade tips and spaced therefrom to define a gas flowpath therebetween, said first annular control member fabricated from a material having a first coefficient of expansion and a first expansion-and-contraction response to temperature variation; a second annular control member radially outward of said first annular control member and fabricated from a material having a second coefficient of expansion and a second expansion-and-contraction response to temperature variation; a radially resilient annular support member resiliently interconnecting said first and second annular control members and having a portion thereof fixed integrally to said first annular control member and another portion thereof fixed integrally to said second annular control member, said first coefficient of expansion being lower than that of said second coefficient of expansion and said first expansion-and-contraction response to temperature being more rapid than said second expansion-and-contraction response.

Claim 21

The blade tip clearance structure of claim 17, wherein the ratio of the second to the first coefficient of expansion is between one and two.

Claim 22

The blade tip clearance structure of claim 18, wherein the ratio of the second to the first coefficient of expansion is between 1.3 and 1.4.

Claim 23

In a gas turbine engine of the type having a rotor mounted for rotation about an axis, a plurality of radially extending blades mounted on the rotor for rotation therewith about the axis, and a support casing surrounding the rotor, a temperature-responsive blade tip clearance structure connected to the support casing and radially spaced from and confronting the blade tips, the clearance control structure comprising: a first annular control member having a surface extending a selected axial length confronting the blade tips and spaced radially therewith to define a gas flowpath therebetween, said first annular control member fabricated from a material having a first coefficient of expansion and a first expansion-and-contraction response to temperature variation; a pair of second annular control members radially outward of said first annular control member and axially spaced relative one another, said second annular control members fabricated from a material having a second coefficient of expansion and a second expansion-and-contraction response to temperature variation; an axially extending radially resilient annular support member having axially spaced portions thereof fixed integrally to a respective one of said second annular control members; said resilient annular support member connected intermediate its axially spaced portions to a portion of said first annular control member intermediate the axial ends thereof to resiliently interconnect said first and second annular control members, said first coefficient of expansion being lower than that of said second coefficient of expansion and said first expansion-and-contraction response to temperature being more rapid than said second expansion-and-contraction response.

Claim 24

In a gas turbine engine of the type having a rotor mounted for rotation about an axis, a plurality of radially extending blades mounted on the rotor for rotation therewith about the axis, and a support casing surrounding the rotor, a temperature-responsive blade tip clearance structure connected to the support casing and radially spaced from and confronting the blade tips, the clearance control structure comprising: a first annular control member having a surface extending a selected axial length confronting the blade tips and spaced radially therewith to define a gas flowpath therebetween, said first annular control member fabricated from a material having a first coefficient of expansion and a first expansion-and-contraction response to temperature variation; a pair of second annular control members radially outward of said first annular control member and axially spaced relative one another, said second annular control members fabricated from a material having a second coefficient of expansion and a second expansion-and-contraction response to temperature variation; an axially extending radially resilient annular support member having axially spaced portions thereof fixed integrally to a respective one of said second annular control members; said resilient annular support member connected intermediate its axially spaced portions to a portion of said first annular control member intermediate the axial ends thereof to resiliently interconnect said first and second annular control members, said first coefficient of expansion being lower than that of said second coefficient of expansion and said first expansion-and-contraction response to temperature being more rapid than said second expansion-and-contraction response.

Claim 25

The blade tip clearance structure of claim 20, further comprising: a radially extending connecting member interconnecting said resilient annular support member intermediate its ends and said first annular control member intermediate its ends, one of said second annular control members located on opposite sides of said radially extending connecting member.

Claim 26

The blade tip clearance structure of claim 20, wherein the ratio of the second to the first coefficient of expansion is between one and two.

Claim 27

The blade tip clearance structure of claim 20, wherein the ratio of the second to the first coefficient of expansion is between 1.3 and 1.4.

Claim 28

The blade tip clearance structure of claim 20, wherein the the axially spaced portions of the resilient annular support member are fixed integrally to their respective ones of said second annular control members by threaded fasteners.