# US 2013/0239587 A1 · Gas turbine engine compressor arrangement > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2013/0239587 A1 - Document ID: US20130239587A1 - Status: Published application - Kind: A1 - Application number: 13/869,057 - Filed: 2013-04-24 - Published: 2013-09-19 - Earliest claimed: 2007-09-21 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Hasel Karl; Joseph B. Staubach; Brian D. Merry; Gabriel L. Suciu; Christopher M. Dye - Web page: https://patentgrep.com/patent/US20130239587A1 ## CPC - F02K 3/025: {the by-pass flow being at least partly used to create an independent thrust component} - F02C 3/107: with two or more rotors connected by power transmission - F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) - F02K 3/06: with front fan - F05D 2260/4031: as in toothed gearing - 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) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine has a fan section, a gear arrangement configured to drive the fan section, a compressor section, including both a low pressure compressor section and a high pressure compressor section. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section is greater than about 35. The pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8. The pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. ## Claims ### Claim 1 A gas turbine engine comprising: a fan section; a gear arrangement configured to drive the fan section; a compressor section, including both a low pressure compressor section and a high pressure compressor section; a turbine section configured to drive the compressor section and the gear arrangement; wherein an overall pressure ratio: provided by the combination of a pressure ratio across the low pressure compressor section and a pressure ratio across the high pressure compressor section; is greater than about 35, wherein the pressure ratio across a first of the low and high pressure compressor sections is between about 3 and about 8, wherein the pressure ratio across a second of the low and high pressure compressor sections is between about 7 and about 15; and wherein the fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. ### Claim 2 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the pressure ratio across the first of the low and high pressure compressor sections being between about 4 and about 6. ### Claim 3 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the pressure ratio across the second of the low and high pressure compressor being between about 8 and about 15. ### Claim 4 (depends on 3) The gas turbine engine as set forth in claim 3, wherein the pressure ratio across the second of the low and high pressure compressor sections being between about 8 and about 10. ### Claim 5 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the overall pressure ratio is above or equal to about 50. ### Claim 6 (depends on 1) The gas turbine engine as set forth in claim 1, wherein a bypass ratio which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section being greater than or equal to about 8. ### Claim 7 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the turbine section includes a low pressure turbine having 4 or 5 stages, and wherein the low pressure turbine drives the low pressure compressor. ### Claim 8 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the turbine section includes a two-stage high pressure turbine, and wherein the high pressure turbine drives the high pressure compressor section. ### Claim 9 (depends on 1) The gas turbine engine as set forth in claim 1, wherein a pressure ratio across the fan section being less than or equal to about 1.45. ### Claim 10 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the first of the low pressure and high pressure compressor sections is the low pressure compressor section. ### Claim 11 (depends on 1) The gas turbine engine as set forth in claim 1, wherein the second of the low and high pressure compressor sections is the high pressure compressor section. ### Claim 12 An arrangement for a gas turbine engine comprising: a fan section having a central axis; a compressor case for housing a compressor; an inlet case for guiding air to the compressor, the compressor case positioned axially further from the fan section than the inlet case; a support member extending between the fan section and the compressor case wherein the support member restricts movement of the compressor case relative to the inlet case; the compressor case includes an upstream compressor case portion and a downstream compressor case portion, the downstream compressor case portion being axially further from the inlet case than the upstream compressor case portion, wherein the support member extends between the fan section and the upstream compressor case portion, and the inlet case is removable from the gas turbofan engine separately from the compressor case; the compressor case includes a low pressure compressor section and a high pressure compressor section. ### Claim 13 A gas turbine engine comprising: a fan section; a compressor section, including both a low pressure compressor section and a high pressure compressor section; and an overall pressure ratio being above or equal to about 35 and being provided by the combination of the low pressure compressor section and the high pressure compressor section, with the overall pressure ratio being provided by a pressure ratio across the low pressure compressor section, and a pressure ratio across the high pressure compressor section, and the pressure ratio across one of the low pressure and high pressure compressor sections being between about 7 and about 15 to provide the overall pressure ratio, wherein the fan delivers a portion of air into the compressor section and a portion of air into a bypass duct, and wherein a pressure ratio across the fan section being less than or equal to about 1.45. ### Claim 14 (depends on 13) The gas turbine engine as set forth in claim 13, wherein the one of the low and high pressure compressor sections is the high pressure compressor section. ### Claim 15 (depends on 14) The arrangement as set forth in claim 14, wherein the pressure ratio across the other of the high and low pressure compressor sections being between about 3 and about 8. ### Claim 16 (depends on 15) The arrangement as set forth in claim 15, wherein the pressure ratio across the other of the low and high pressure compressor sections being between about 4 and about 6. ### Claim 17 (depends on 13) The arrangement as set forth in claim 13, wherein the pressure ratio across the one of the low and high pressure compressor sections being between about 8 and about 15. ### Claim 18 (depends on 19) The arrangement as set forth in claim 19, wherein the pressure ratio across the one of the low and high pressure compressor sections being between about 8 and about 10. ### Claim 19 (depends on 13) The arrangement as set forth in claim 13, wherein a bypass ratio is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section being greater than or equal to about 8.