Stator seal assembly providing improved clearance control

In a gas turbine engine of a type having a high pressure compressor section with a stator vane, said stator vane having a support structure, and a rotor disk, said rotor disk having a plurality of radially-outwardly extending seal teeth, a stator seal assembly comprising:

• a stator seal segment extending between said stator vane support structure and said rotor disk seal teeth;
• said stator seal segment having a forward arm for forming a cavity;
• a retaining segment for sealing said cavity to form a dead air space;
• a control ring located in said cavity for controlling thermal growth of said stator seal segment, whereby thermal expansion clearance between said stator vane and said rotor disk is minimized by said control ring at both steady state and during transient operation of said engine;
• a relatively thick honeycomb block located between said stator seal forward arm and said rotor disk seal teeth;
• wherein said control ring comprises a material having a lower coefficient of thermal expansion than a coefficient of thermal expansion for said seal segment;
• wherein said control ring is a titanium aluminide alloy;
• wherein said forward arm and said control ring have means for positioning said control ring within said cavity;
• wherein said means for positioning said control ring comprises a groove located in said forward arm and a downwardly extending flange from said control ring.

In a gas turbine engine of a type having a turbine section with a first state turbine disk having a forward seal assembly, said forward seal assembly including a plurality of radially outwardly extending seal teeth, and a stator vane, said stator vane having a support structure, a stator seal assembly comprising:

• a stator seal segment extending between said stator vane support structure and said seal teeth;
• said stator seal segment having an aft arm for forming a cavity;
• a retaining segment for sealing and shielding said cavity;
• a control ring located in said cavity for controlling thermal growth of said stator seal segment, whereby thermal expansion clearance between said stator vane and said turbine disk is minimized by said control ring;
• and
• a honeycomb block located between said aft arm and said seal teeth;
• wherein said control ring comprises an alloy having a coefficient of thermal expansion lower than a coefficient of thermal expansion of said seal segment;
• wherein said control ring is a titanium aluminide alloy;
• wherein said aft arm and said control ring have means for positioning said control ring within said cavity;
• wherein said means for positioning said control ring comprises a groove located in said aft arm and a downwardly extending flange from said control ring.

In a gas turbine engine of a type having a compressor section with a rotor disk and a stator vane, and a turbine section with a stator vane and a turbine disk forward seal assembly, a stator seal assembly comprising:

• a first stator seal positioned between said compressor rotor disk and said compressor stator vane;
• said first stator having a seal member extending from said stator vane and including means for forming a cavity, means for sealing said cavity, and a control ring positioned in said cavity;
• said control ring having a lower coefficient of thermal expansion than a coefficient of thermal expansion of said seal member, thereby controlling thermal growth of said seal member;
• and
• a second stator seal positioned between said turbine stator vane and said forward seal assembly;
• said second stator seal having a seal member extending from said stator vane and including means for forming a cavity, means for sealing said cavity, and a control ring positioned in said cavity;
• said control ring having a lower coefficient of thermal expansion than a coefficient of thermal expansion of said seal member, thereby controlling thermal growth of said seal member;
• wherein said means for forming said cavity of said first stator seal is a forward arm, wherein said control ring of said first stator seal includes a pair of axially spaced apart and radially inward lands, each of said lands directly contacting a radially outward surface of said forward arm.

In a gas turbine engine of a type having a compressor section with a rotor disk and a stator vane, and a turbine section with a stator vane and a turbine disk forward seal assembly, a stator seal assembly comprising:

• a first stator seal positioned between said compressor rotor disk and said compressor stator vane;
• said first stator seal having a seal member extending from said stator vane and including means for forming a cavity, means for sealing said cavity, and a control ring positioned in said cavity;
• said control ring having a lower coefficient of thermal expansion than a coefficient of thermal expansion of said seal member, thereby controlling thermal growth of said seal member;
• and
• a second stator seal positioned between said turbine stator vane and said forward seal assembly;
• said second stator seal having a seal member extending from said stator vane and including means for forming a cavity, means for sealing said cavity, and a control ring positioned in said cavity;
• said control ring having a lower coefficient of thermal expansion than a coefficient of thermal expansion of said seal member, thereby controlling thermal growth of said seal member;
• wherein said means for forming said cavity of said first stator seal is a forward arm;
• wherein said means for sealing said cavity of said first stator seal is a retainer member fastened to said seal member and said forward arm.

In a gas turbine engine of a type having a compressor with a rotor disk and a stator vane, and a turbine section with a stator vane and a turbine disk forward seal assembly, a stator seal assembly comprising:

• a first stator seal positioned between said compressor rotor disk and said compressor stator vane;
• said first stator seal having a seal member extending from said stator vane and including means for forming a cavity, means for sealing said cavity, and a control ring positioned in said cavity;
• said control ring having a lower coefficient of thermal expansion than a coefficient of thermal expansion of seal member, thereby controlling thermal growth of said seal member;
• and
• a second stator seal positioned between said turbine stator vane and said forward seal assembly;
• said second stator seal having a seal member extending from said stator vane and including means for forming a cavity, means for sealing said cavity, and a control ring positioned in said cavity;
• said control ring having a lower coefficient of thermal expansion than a coefficient of thermal expansion of said seal member, thereby controlling thermal growth of said seal member;
• wherein said means for forming said cavity of said second stator seal is an aft arm;
• wherein said means for sealing said cavity of said second stator seal is a retainer member fastened to said seal member and said aft arm.