# US 10,119,466 B2 · Geared turbofan engine with high compressor exit temperature > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,119,466 B2 - Document ID: US10119466B2 - Status: Granted - Kind: B2 - Application number: 14/950,393 - Filed: 2015-11-24 - Published: 2016-03-17 - Granted: 2018-11-06 - Earliest claimed: 2012-10-02 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Frederick M. Schwarz; Karl L. Hasel - Web page: https://patentgrep.com/patent/US10119466B2 ## CPC - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F02C 3/06: the compressor comprising only axial stages (F02C3/10 takes precedence) - F02K 3/06: with front fan - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis. ## Claims ### Claim 1 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between 1000° F. and 1500° F.; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor; a geared architecture driven by the turbine section for rotating the fan about the axis, wherein the geared architecture is positioned upstream of a low pressure turbine and downstream of a compressor rotor of the first compressor section driven by the low pressure turbine; and an inducer forming an additional compression section positioned upstream of the first and second compressor sections. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1 wherein the average exit temperature is between 1100° F. and 1450° F. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1 wherein the first compressor section comprises a low pressure compressor and the second compressor section comprises a high pressure compressor, and wherein the turbine section comprises a low pressure turbine that drives the low pressure compressor via a first shaft and a high pressure turbine that drives the high pressure compressor via a second shaft, and wherein the geared architecture couples the first shaft to the fan. ### Claim 4 (depends on 1) The gas turbine engine as set forth in claim 1 wherein the average exit temperature is defined at sea level, end of takeoff power and at a rated thrust for the gas turbine engine. ### Claim 5 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section and a second compressor section, wherein the first compressor section comprises a low pressure compressor and the second compressor section comprises a high pressure compressor, and wherein components of the second compressor section are configured to operate at an average exit temperature that is between 1000° F. and 1500° F.; wherein the high pressure compressor includes a plurality of stages with each stage comprising a disk with a plurality of blades extending radially outwardly from a rim of the disk, and wherein the plurality of stages includes at least a first stage having a first blade and disk configuration and a second stage having a second blade and disk configuration that is different than the first blade and disk configuration, and wherein the first blade and disk configuration comprises a plurality of slots to receive the plurality of blades and including a plurality of rim cavities for honeycomb seals, and wherein the second blade and disk configuration comprises integrally formed blades such that there are no rim cavities or associated honeycomb seals; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor; and a geared architecture driven by the turbine section for rotating the fan about the axis, and wherein the turbine section comprises a low pressure turbine that drives the low pressure compressor via a first shaft and a high pressure turbine that drives the high pressure compressor via a second shaft, and wherein the geared architecture couples the first shaft to the fan. ### Claim 6 (depends on 5) The gas turbine engine according to claim 5 wherein the first stage is positioned forward of the second stage. ### Claim 7 (depends on 5) The gas turbine engine as set forth in claim 5, wherein the geared architecture is positioned intermediate the fan and a compressor rotor driven by a low pressure turbine. ### Claim 8 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between 1000° F. and 1500° F.; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor, wherein the turbine section comprises three separate turbine sections including a fan drive turbine, an intermediate pressure turbine, and a secondary pressure turbine; the intermediate pressure turbine driving a first compressor rotor of the first compressor section; the secondary pressure turbine driving a second compressor rotor of the second compressor section; and a geared architecture driven by the fan drive turbine for rotating the fan about the axis. ### Claim 9 (depends on 8) The gas turbine engine according to claim 8 wherein the first compressor section comprises a low pressure compressor and the second compressor section comprises a high pressure compressor, and wherein the fan drive turbine drives the geared architecture via a shaft, and wherein the intermediate pressure turbine is configured to drive the first compressor rotor, and the secondary pressure turbine is configured to drive the second compressor rotor. ### Claim 10 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section rotating at a first speed and a second compressor section rotating at a second speed greater than the first speed, wherein components of the second compressor section are configured to operate at an average exit temperature that is between 1000° F. and 1500° F.; the second compressor section including a plurality of stages with each stage comprising a disk with a plurality of blades extending radially outwardly from a rim of the disk, and wherein the plurality of stages includes at least a first stage having a first blade and disk configuration and a second stage having a second blade and disk configuration that is different than the first blade and disk configuration, and wherein the first blade and disk configuration comprises a plurality of slots to receive the plurality of blades and including a plurality of rim cavities for honeycomb seals, and wherein the second blade and disk configuration comprises integrally formed blades such that there are no rim cavities or associated honeycomb seals; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor, wherein the turbine section comprises a first turbine section that drives the first compressor section via a first shaft at the first speed and a second turbine section that drives the second compressor section via a second shaft at the second speed; and a geared architecture driven by the turbine section for rotating the fan about the axis, and wherein the geared architecture couples the first shaft to the fan. ### Claim 11 (depends on 10) The gas turbine engine according to claim 10 wherein the average exit temperature of the second compressor section is between 1100° F. and 1450° F. ### Claim 12 (depends on 10) The gas turbine engine according to claim 10 wherein the first stage is positioned forward of the second stage. ### Claim 13 (depends on 10) The gas turbine engine according to claim 10 wherein the average exit temperature is defined at Sea Level, end of takeoff power and at a rated thrust for the gas turbine engine. ### Claim 14 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section rotating at a first speed and a second compressor section rotating at a second speed greater than the first speed, wherein components of the second compressor section are configured to operate at an average exit temperature that is between 1000° F. and 1500° F.; the second compressor section including a plurality of stages with each stage comprising a disk with a plurality of blades extending radially outwardly from a rim of the disk, and wherein the plurality of stages includes at least a first stage having a first blade and disk configuration and a second stage having a second blade and disk configuration that is different than the first blade and disk configuration; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor, wherein the turbine section comprises a first turbine section that drives the first compressor section via a first shaft at the first speed and a second turbine section that drives the second compressor section via a second shaft at the second speed; a geared architecture driven by the turbine section for rotating the fan about the axis, and wherein the geared architecture couples the first shaft to the fan; and an inducer forming an additional compression section positioned in front of the first and second compressor sections. ### Claim 15 (depends on 14) The gas turbine engine according to claim 14 wherein the inducer is configured to rotate at a speed common with that of the fan. ### Claim 16 A gas turbine engine comprising: a fan including a plurality of fan blades rotatable about an axis; a compressor section including at least a first compressor section rotating at a first speed and a second compressor section rotating at a second speed greater than the first speed, wherein components of the second compressor section are configured to operate at an average exit temperature that is between 1000° F. and 1500° F.; a combustor in fluid communication with the compressor section; a turbine section in fluid communication with the combustor; a geared architecture driven by the turbine section for rotating the fan about the axis; an inducer forming an additional compression section positioned in front of the first and second compressor sections, wherein the inducer is configured to rotate at a higher speed than the fan through an additional output of the geared architecture.