Cyclonic separator for seal support
AssigneeRtx Corporation
InventorsMichael G. McCaffrey, Paul M. Lutjen
Life of this patent
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Abstract
A separator system for a blade outer air seal cooling passage of a gas turbine engine includes a cooling passage defined between an engine casing on a radially outer boundary and alternating blade outer air seals and vanes on a radially inner boundary; and a support positioned along the cooling passage and dividing the cooling passage into an upstream portion and a downstream portion of the cooling passage; wherein the support further includes at least one cyclonic separator having a flow inlet opening to the upstream portion, and having a filtered air outlet feeding to the downstream portion, and a particulate outlet for particles separated from flow through the cyclonic separator.
Claims18
A separator system for a blade outer air seal cooling passage of a gas turbine engine, comprising:
- a cooling passage defined between an engine casing on a radially outer boundary and alternating blade outer air seals and vanes on a radially inner boundary;
- and
- a support positioned along the cooling passage and dividing the cooling passage into an upstream portion and a downstream portion;
- wherein the support further comprises at least one cyclonic separator having a flow inlet opening to the upstream portion, and having a filtered air outlet feeding to the downstream portion, and a particulate outlet for particles separated from flow through the cyclonic separator, wherein the blade outer air seals comprises a plurality of blade outer air seals including a first upstream blade outer air seal, and wherein the support is axially positioned upstream of the first upstream blade outer air seal, and wherein the vanes comprise a plurality of vanes alternatingly positioned between rotors that seal against the plurality of blade outer air seals, and wherein the support is axially positioned downstream of a first vane of the plurality of vanes and upstream of a second vane of the plurality of vanes.
A separator system for a blade outer air seal cooling passage of a gas turbine engine, comprising:
- a cooling passage defined between an engine casing on a radially outer boundary and alternating blade outer air seals and vanes on a radially inner boundary;
- and
- a support positioned along the cooling passage and dividing the cooling passage into an upstream portion and a downstream portion;
- wherein the support further comprises at least one cyclonic separator having a flow inlet opening to the upstream portion, and having a filtered air outlet feeding to the downstream portion, and a particulate outlet for particles separated from flow through the cyclonic separator, wherein the blade outer air seals comprises a plurality of blade outer air seals including a first upstream blade outer air seal, and wherein the support is axially positioned upstream of the first upstream blade outer air seal wherein the filtered air outlet is connected to a vane cooling space defined between a vane outer flange and the engine casing.
Dependencies are inferred from the claim text.