# US 10,480,519 B2 · Hybrid compressor > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,519 B2 - Document ID: US10480519B2 - Status: Granted - Kind: B2 - Application number: 15/081,419 - Filed: 2016-03-25 - Published: 2016-10-06 - Granted: 2019-11-19 - Earliest claimed: 2015-03-31 - Assignees: Rolls-Royce North American Technologies Inc. - Applicants: Rolls-Royce North American Technologies, Inc. - Inventors: William B. Bryan - Web page: https://patentgrep.com/patent/US10480519B2 ## CPC - F04D 19/028: {Layout of fluid flow through the stages} - F01D 5/045: {the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations} - F01D 5/048: {Form or construction} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F04D 17/025: {comprising axial flow and radial flow stages} - F05D 2220/40: in turbochargers - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A compressor for a gas turbine engine is disclosed. The compressor includes a first compression stage mounted for rotation about a central axis that includes a plurality of first-stage blades. The compressor also includes a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage. The second compression stage includes a plurality of second-stage blades. ## Claims ### Claim 1 A compressor for a gas turbine engine, the compressor comprising a first compression stage mounted for rotation about a central axis, the first compression stage including a plurality of first-stage blades, and a second compression stage mounted for rotation along the central axis aft of the first compression stage to receive air compressed by the first compression stage, the second compression stage including a plurality of second-stage blades, the second compression stage shaped to conduct air in a substantially radial direction away from the central axis and to discharge air in a substantially axial direction parallel to the central axis, wherein an average exit radius of the plurality of first stage-blades is greater than an inlet tip radius of the plurality of first-stage blades. ### Claim 2 (depends on 1) The compressor of claim 1, wherein the average exit radius of the plurality of second-stage blades is greater than the inlet tip radius of the plurality of second stage-blades. ### Claim 3 (depends on 1) The compressor of claim 1, further comprising a diffuser mounted aft of an outlet of the second compression stage along the central axis, the diffuser shaped to conduct air in substantially only the axial direction parallel to the central axis. ### Claim 4 (depends on 3) The compressor of claim 3, wherein the diffuser comprises a first outlet guide vane aligned with the outlet of the second compression stage in the axial direction to receive air discharged in the axial direction parallel to the central axis by the outlet of the second compression stage and to conduct air from the outlet of the second compression stage in only the axial direction parallel to the central axis. ### Claim 5 (depends on 4) The compressor of claim 4, wherein the diffuser further comprises a second outlet guide vane aligned with the first outlet guide vane in the axial direction to receive air discharged in the axial direction parallel to the central axis by the first outlet guide vane and to conduct air from the first outlet guide vane in only the axial direction parallel to the central axis. ### Claim 6 (depends on 5) The compressor of claim 5, wherein the second outlet guide vane is spaced from the first outlet guide vane in the axial direction without a rotating component being positioned between the first and second outlet guide vanes. ### Claim 7 (depends on 1) The compressor of claim 1, further comprising an interstage vane mounted between the first compression stage and the second compression stage along the central axis, the interstage vane shaped to redirect air exiting the first compression stage in the axial and radial directions before the air enters the second compression stage. ### Claim 8 (depends on 1) The compressor of claim 1, wherein (i) the first compression stage is supported by a first shaft extending along the central axis and (ii) the second compression stage is supported by a second shaft separate from the first shaft extending along the central axis. ### Claim 9 A compressor for a gas turbine engine, the compressor comprising a first compression stage mounted for rotation about a central axis, the first compression stage including a plurality of first-stage blades, wherein an average exit radius of the plurality of first stage-blades is greater than an inlet tip radius of the plurality of first-stage blades, and a second compression stage mounted for rotation along the central axis aft of the first compression stage, the second compression stage including a plurality of second-stage blades, the second-stage blades each having an inlet portion that has an inlet hub radius and an inlet tip radius, an outlet portion shaped to discharge air in a substantially axial direction parallel to the central axis that has an outlet hub radius and an outlet tip radius, and an average exit radius substantially midway between the outlet hub radius and the outlet tip radius that is greater than the inlet tip radius. ### Claim 10 (depends on 9) The compressor of claim 9, wherein each of the plurality of second-stage blades includes a radial-compression portion shaped to conduct air in a substantially radial direction away from the central axis. ### Claim 11 (depends on 9) The compressor of claim 9, wherein the inlet tip radius of the inlet portions of the second-stage blades is less than the average exit radius of the outlet portions of the second-stage blades. ### Claim 12 (depends on 11) The compressor of claim 11, further comprising a diffuser mounted aft of the outlet portions of the second compression stage along the central axis and shaped to conduct air in substantially only the axial direction parallel to the central axis. ### Claim 13 (depends on 12) The compressor of claim 12, wherein the diffuser comprises a first outlet guide vane aligned with the outlet portions of the second-stage blades in the axial direction to receive air discharged in the axial direction parallel to the central axis and to conduct air from the outlet portions in substantially only the axial direction parallel to the central axis. ### Claim 14 (depends on 12) The compressor of claim 12, wherein the diffuser comprises (i) a first outlet guide vane aligned with the outlet portions of the second-stage blades in the axial direction to receive air discharged from the second compression stage and to conduct air from the outlet portions in substantially only the axial direction parallel to the central axis, and (ii) a second outlet guide vane aligned with the first outlet guide vane in the axial direction to receive air discharged in the axial direction from the first outlet guide vane and to conduct air from the first outlet guide vane in substantially only the axial direction parallel to the central axis. ### Claim 15 (depends on 14) The compressor of claim 14, wherein the second outlet guide vane is spaced from the first outlet guide vane in the axial direction without a rotating component being positioned between the first and second outlet guide vanes. ### Claim 16 (depends on 12) The compressor of claim 12, further comprising an interstage vane mounted between the first compression stage and the second compression stage along the central axis, the interstage vane shaped to redirect air exiting the first compression stage in the axial and radial directions toward the second compression stage. ### Claim 17 (depends on 12) The compressor of claim 12, wherein (i) the first compression stage is supported by a first shaft extending along the central axis and (ii) the second compression stage is supported by a second shaft separate from the first shaft extending along the central axis.