SEAL RING

A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe. 1. A seal , comprising: 'a first petal extending radially inward with respect to the first central axis of the first seal ring;', 'a first seal ring having a first central axis, the first seal ring comprising 'a second petal axially proximate the first petal, offset from the first petal in a circumferential direction, and extending radially inward with respect to the second central axis of the second seal ring;', 'a second seal ring having a second central axis substantially equal to the first central axis, the second seal ring comprising;'}a sealing disk axially proximate the second seal ring and having a seal shoe configured as a primary seal, wherein the second petal extends toward the seal shoe.2. The seal of claim 1 , wherein the first seal ring comprises a first plurality of separate segments and the second seal ring comprises a second plurality of separate segments.3. The seal of claim 1 , wherein the second seal ring further comprises a lip configured to engage the seal shoe.4. The seal of claim 1 , wherein the first seal ring is on a high-pressure side in a gas turbine engine and the second seal ring is on a low-pressure side in ...

INNER STAGE TURBINE SEAL FOR GAS TURBINE ENGINE

A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal. 1. A turbine section of a gas turbine engine , comprising:a vane platform;a Blade Outer Air Seal; anda seal that extends between said vane platform and said Blade Outer Air Seal.2. The turbine section as recited in claim 1 , further comprising a vane support that at least partially supports a multiple of said vane platforms.3. The turbine section as recited in claim 2 , further comprising a Blade Outer Air Seal support that at least partially supports a multiple of said Blade Outer Air Seals.4. The turbine section as recited in claim 2 , further comprising a Blade Outer Air Seal support that extends from said vane support claim 2 , said Blade Outer Air Seal support at least partially supports said Blade Outer Air Seal.5. The turbine section as recited in claim 3 , further comprising a radial wall of said vane support that extends at least partially between said vane platform and said Blade Outer Air Seal support.6. The turbine section as recited in claim 5 , wherein said radial wall of said vane support extends toward said seal.7. The turbine section as recited in claim 6 , wherein said seal is mounted to said Blade Outer Air Seal support.8. The turbine section as recited in claim 7 , wherein said Blade Outer Air Seal support includes a multiple of circumferentially arranged lugs.9. The turbine section as recited in claim 1 , wherein said seal is a brush seal.10. A turbine section of a gas turbine engine claim 1 , comprising:a vane support including a radial wall;a Blade Outer Air Seal support; anda seal mounted to said Blade Outer Air Seal support, said seal extends axially beyond an end section of said radial wall.11. The turbine section as recited in claim 10 , wherein said seal extends between a vane platform and a Blade Outer Air Seal.12. The turbine section as recited in claim 11 , wherein said vane support at least partially supports said ...

TURBINE CLEARANCE CONTROL SYSTEM AND METHOD FOR IMPROVED VARIABLE CYCLE GAS TURBINE ENGINE FUEL BURN

A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed. 120-. (canceled)21. A gas turbine engine comprising:a flow circuit from a second stream airflow path of the gas turbine engine to communicate a portion of an airflow from said second stream airflow path to a heat exchanger;a flow circuit from said heat exchanger to eject said portion of said airflow of said second stream airflow path into a third stream airflow path;a flow circuit from a primary airflow path of the gas turbine engine to communicate a portion of said core airflow from said primary airflow path to said heat exchanger; anda flow circuit from said heat exchanger to eject said portion of said core airflow from said cooled cooling air system as a cooled cooling airflow to a high pressure turbine section of the gas turbine engine to limit a transient pinch event thereby reducing a steady state radial tip clearance during engine operation.22. The gas turbine engine as recited in claim 21 , wherein said flow circuit from said primary airflow path of the gas turbine engine communicates with a diffuser in a combustor section.23. The gas turbine engine as recited in claim 21 , wherein the radial running tip clearance is defined between a turbine airfoil and a shroud assembly during engine operation.24. The gas turbine engine as recited in claim 21 , further comprising selectively supplying the cooled cooling air in response to an engine rotor speed.25. The gas turbine engine as recited in claim 21 , wherein the second stream airflow from the second stream airflow path is ejected from the air-to-air heat exchanger system to the third stream airflow path.26. The gas turbine engine as recited in claim 21 , wherein the transient pinch event occurs when the ...

BRUSH SEAL PLATE

A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin. 1. A brush seal plate system , comprising:a flat ring comprising an inner diameter defining a central opening; anda bristle protruding from the inner diameter of the flat ring into the central opening.2. The brush seal plate system of claim 1 , further comprising a racetrack slot configured to allow the flat ring to move in a radial direction relative to a retention pin.3. The brush seal plate system of claim 1 , wherein the bristle protrudes radially inward from the inner diameter at an angle relative to a radial line passing through the bristle.4. The brush seal plate system of claim 1 , further comprising a split formed through the flat ring.5. The brush seal plate system of claim 4 , wherein the split is angled relative to radial line passing through the split.6. The brush seal plate system of claim 1 , wherein the flat ring is circumferentially discontinuous.7. The brush seal plate system of claim 1 , wherein the flat ring further comprises a retention opening configured to fix the flat ring in place relative to a retention pin.8. A seal comprising:a brush seal plate;a bristle extending radially inward from an inner diameter of the brush seal plate; anda sealing disk axially proximate the brush seal plate, wherein the bristle extends towards a seal shoe of the sealing disk.9. The seal of claim 8 , further comprising:a retention opening in the brush seal plate; anda spacer adjacent the brush seal plate ...

NON-CONTACTING DYNAMIC SEAL

Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam. 1. A seal for a gas turbine engine comprising:a full hoop outer ring;a shoe coupled to the full hoop outer ring via an inner beam and an outer beam; anda wave spring in contact with at least one of the inner beam or the outer beam.2. The seal of claim 1 , wherein the wave spring is located between the inner beam and the outer beam.3. The seal of claim 1 , wherein the wave spring is located between the shoe and the inner beam.4. The seal of claim 1 , wherein the wave spring is located between the outer beam and the full hoop outer ring.5. The seal of claim 1 , wherein the wave spring comprises at least three antinodes.6. The seal of claim 5 , wherein the antinodes are configured to slide against at least one of the inner beam or the outer beam in response to a vibration in the seal.7. The seal of claim 1 , wherein the seal is a non-contacting dynamic seal.8. The seal of claim 1 , further comprising a plurality of inner segments claim 1 , wherein each inner segment comprises a respective wave spring.9. A seal assembly for a gas turbine engine comprising:an outer ring;a shoe coupled to the outer ring, wherein the shoe is configured to move radially with respect to the outer ring;a first beam and a second beam coupling the shoe to the outer ring; anda first wave spring located between the first beam and the second beam, wherein the first wave spring is configured to damp vibrations in the first beam and the second beam.10. The seal assembly of claim 9 , wherein the seal assembly is a non-contacting dynamic seal.11. The seal assembly of claim 9 , wherein the first wave ...

Seal ring

A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

SEAL SUPPORT STRUCTURE

The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement. 1. A seal support structure for a gas turbine engine , the seal support structure comprising:a seal support configured to retain a circumferential seal; andan engine support configured for mounting the seal support structure to a gas turbine engine mount, wherein the engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support.2. The seal support structure of claim 1 , wherein the seal support includes a runner and a shoulder configured to retain the circumferential seal.3. The seal support structure of claim 1 , wherein each channel is configured to receive a retaining element of the engine mount.4. The seal support structure of claim 1 , wherein each channel is an elongated slot oriented in a radial direction to provide radial motion for the seal support and engine support.5. The seal support structure of claim 1 , wherein radial movement of the seal support structure includes radial movement of the seal support structure relative to a static gas turbine engine mount claim 1 , wherein radial movement includes movement to and away from a rotating component.6. The seal support structure of claim 1 , wherein circumferential retention of the seal support includes retaining claim 1 , by the seal support structure claim 1 , a circumferential seal ...

Seal support structure for a circumferential seal of a gas turbine engine

A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

Gas turbine engine and seal assembly therefore

The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.

NON-CONTACTING DYNAMIC SEAL

A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam. 1. A seal for a gas turbine engine comprising:a full hoop outer ring;a shoe coupled to the full hoop outer ring via an inner beam and an outer beam; anda wave spring in contact with at least one of the inner beam or the outer beam.2. The seal of claim 1 , wherein the wave spring is located between the inner beam and the outer beam.3. The seal of claim 1 , wherein the wave spring is located between the shoe and the inner beam.4. The seal of claim 1 , wherein the wave spring is located between the outer beam and the full hoop outer ring.5. The seal of claim 1 , wherein the wave spring comprises at least three antinodes.6. The seal of claim 5 , wherein the antinodes are configured to slide against at least one of the inner beam or the outer beam in response to a vibration in the seal.7. The seal of claim 1 , wherein the seal is a non-contacting dynamic seal.8. The seal of claim 1 , further comprising a plurality of inner segments claim 1 , wherein each inner segment comprises a respective wave spring.9. The seal of claim 1 , wherein the shoe is configured to move radially with respect to the outer ring.10. The seal of claim 9 , wherein the inner beam is disposed radially from the outer beam.11. The seal of claim 10 , wherein the wave spring is located radially between the inner beam and the outer beam.12. The seal of claim 10 , wherein the wave spring is located radially between the shoe and the inner beam.13. The seal of claim 10 , wherein the wave spring is located radially between the outer beam and the full hoop outer ring. This application is a divisional of, and claims priority to, and the benefit of U.S. application Ser. No. 14/852,838, entitled “NON-CONTACTING DYNAMIC SEAL,” filed on Sep. 14, 2015, which is a nonprovisional of, and ...

METHOD OF MAKING AIRFOILS

A method of method of making an airfoil includes making a refractory metal core that defines an interior of the airfoil by a tomo-lithographic process, making a mold that defines an exterior of the airfoil, inserting the refractory metal core into the mold, and pouring an airfoil material between the refractory metal core and the mold to cast the airfoil. 1. A method of making an airfoil , the method comprising:making a refractory metal core that defines an interior of the airfoil by a tomo-lithographic process;making a mold that defines an exterior of the airfoil;inserting the refractory metal core into the mold; andpouring an airfoil material between the refractory metal core and the mold to cast the airfoil.2. The method of claim 1 , further comprising:removing the airfoil from the mold; andremoving the core from the airfoil.3. The method of claim 2 , wherein removing the core from the airfoil comprises applying an acid treatment.4. The method of claim 1 , further comprising:applying a ceramic coating to the refractory metal core prior to pouring the airfoil material.5. The method of claim 1 , wherein the refractory metal core comprises one of the following materials: molybdenum claim 1 , tantalum claim 1 , niobium claim 1 , or tungsten.6. The method of claim 1 , wherein the tomo-lithographic process comprises:forming a first layer of the refractory metal core out of a first material;forming a second layer of the refractory metal core out of the first material;bonding the first and second layers together to form a laminate master pattern;forming a flexible mold around the laminate master pattern;removing the laminate master pattern from the flexible mold;pouring a pulverulent refractory metal material mixed with a binder into the flexible mold; andsintering the pulverulent refractory metal material in an oxygen-free environment to form the refractory metal core.7. The method of claim 4 , further comprising:applying a metallic layer to the refractory metal core.8. ...

Turbine clearance control system and method for improved variable cycle gas turbine engine fuel burn

A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

SEAL SUPPORT STRUCTURE FOR A CIRCUMFERENTIAL SEAL OF A GAS TURBINE ENGINE

A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

Apparatus for and method of making multi-walled passages in components

HOUSING FOR A ROTATING MACHINE, PARTICULARLY FOR A TURBOMOTOR, AND ITS ASSEMBLY METHOD

Turbine clearance control system and method for improved variable cycle gas turbine engine fuel burn

A method of assembling a gas turbine engine (20) includes setting a build clearance at assembly in response to a running tip clearance (108) defined with a cooled cooling air. Another method of operating a gas turbine engine (20) includes supplying a cooled cooling air to a high pressure turbine (32) in response to an engine rotor speed. A corresponding gas turbine engine (20) comprising a turbine clearance control, wherein a part of the core flow (60) is bled to be cooled in a heat exchanger (70) and then directed to the high pressure turbine section (32), wherein the heat exchanger cooling flow is a first by pass flow (58) coming from a second fan stage section and then directed to a second by pass flow (56) coming from a first stage fan section.

Seal ring

A seal ring system is provided. The seal ring system comprises a segment (202; 402) defining a slot (208; 308), a petal (214; 312; 408) along the slot (208; 308), and an opening (204; 304; 404; 522) offset from the slot (208; 308). A retention fastener may be disposed in the opening (204; 304; 404; 522). A seal ring system is also provided comprising a first segment (202; 402) defining a first opening (204; 304; 404; 522), a second segment (216; 314; 410) defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment (202; 402) and the second segment (216; 314; 410). A seal (500; 600; 700) is further provided comprising a seal ring (200; 300; 400) having a central axis, a petal (214; 312; 408) extending radially inward with respect to the central axis of the seal ring (200; 300; 400), and a sealing disk axially proximate the seal ring (200; 300; 400). The sealing disk may have a seal shoe (512; 608; 710) configured as a primary seal. The petal (214; 312; 408) may extend toward the seal shoe (512; 608; 710).

Lightning arrester monitor

Brush seal plate

Non-contacting dynamic seal

A method of damping vibrations in a seal includes inserting a first wave spring between a first beam and a second beam of the seal. The seal can be for a gas turbine engine and can include a full hoop outer ring, a shoe coupled to the full hoop outer ring via the first beam (e.g., an outer beam) and the second beam (e.g., an inner beam), and the first wave spring in contact with the first beam and the second beam.

Device for perforating and sorting indicia bearing cards

Brush seal plate

A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.

Inner stage turbine seal for gas turbine engine

A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.