# US 2019/0170353 A1 · Compressor diffuser and gas turbine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0170353 A1 - Document ID: US20190170353A1 - Status: Published application - Kind: A1 - Application number: 16/095,859 - Filed: 2017-04-17 - Published: 2019-06-06 - Earliest claimed: 2016-04-25 - Assignees: Mitsubishi Heavy Industries, Ltd. - Applicants: Mitsubishi Heavy Industries, Ltd. - Inventors: Kuniaki AOYAMA; Hiroyuki YAMAMOTO - Web page: https://patentgrep.com/patent/US20190170353A1 ## CPC - F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) - F23R 3/10: for primary air (F23R3/06, F23R3/045 take precedence) - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F02C 7/04: Air intakes for gas-turbine plants or jet-propulsion plants - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F23R 3/04: Air inlet arrangements - F23R 3/46: Combustion chambers comprising an annular arrangement of {several essentially tubular} flame tubes within a common annular casing or within individual casings - 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) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## Abstract A compressor diffuser is disposed between cylindrical combustion chambers that are disposed around a rotational shaft to supply combustion gas to a turbine and a compressor that is rotatable about the rotational shaft to generate compressed air. The compressor diffuser includes one end connected to an outlet of the compressor; and another end connected to an air inlet of one of the combustion chambers. The one end defines an opening and has double arc portions curving about the rotational shaft, and the other end defines an opening shaped in conformance with the cylindrical shape of the one of the combustion chambers. The compressor diffuser is disposed continuously along an extending direction of the rotational shaft from the one end to the other end. ## Claims ### Claim 1 A compressor diffuser disposed between cylindrical combustion chambers that are disposed around a rotational shaft to supply combustion gas to a turbine and a compressor that is rotatable about the rotational shaft to generate compressed air, the compressor diffuser comprising: one end connected to an outlet of the compressor; and the other end connected to an air inlet of one of the combustion chambers, the one end defining an opening and having double arc portions curving about the rotational shaft, the other end defining an opening shaped in conformance with the cylindrical shape of the one of the combustion chambers, wherein the compressor diffuser is disposed continuously along an extending direction of the rotational shaft from the one end to the other end. ### Claim 2 (depends on 1) The compressor diffuser according to claim 1 comprising an inner member with which the one end has a single-annular outline and the other end has a double-annular outline. ### Claim 3 (depends on 1) The compressor diffuser according to claim 1 comprising a separating member that divides a path into two paths that are continuous from the one end to the other end. ### Claim 4 (depends on 1) The compressor diffuser according to claim 1, comprising an air bleed port disposed at at least one of the one end and the other end to bleed the compressed air. ### Claim 5 (depends on 1) The compressor diffuser according to claim 1, wherein the compressor diffuser accommodates a vane inside the one end, the vane being disposed at the outlet of the compressor, the compressor diffuser having side walls, which are close to the one end, in a turbine radial direction to divide a flow path in a turbine circumferential direction, the portions being shaped in conformance with a shape of the vane. ### Claim 6 (depends on 1) The compressor diffuser according to claim 1, wherein the one end has side portions each corresponding to a rear end of a vane disposed at the outlet of the compressor. ### Claim 7 (depends on 1) The compressor diffuser according to claim 1, wherein the other end is inserted in the combustion chamber and the one end is mounted to the outlet of the compressor via a mounting flange. ### Claim 8 (depends on 1) The compressor diffuser according to claim 1, wherein the other end is integrally formed with the combustion chamber, and the one end is mounted to the outlet of the compressor via a mounting flange. ### Claim 9 (depends on 1) The compressor diffuser according to claim 1, wherein the compressor diffuser is mounted via a supporting member in a combustor casing chamber in which the combustion chamber is disposed with the other end being inserted in the combustion chamber and the one end abutting the outlet of the compressor. ### Claim 10 (depends on 1) The compressor diffuser according to claim 1, wherein the compressor diffuser is mounted via a supporting member in a combustor casing chamber in which the combustion chamber is disposed with the other end being integrally formed with the combustion chamber and the one end abutting the outlet of the compressor. ### Claim 11 (depends on 1) A gas turbine comprising: a turbine disposed about a rotational shaft; cylindrical combustion chambers arranged around the rotational shaft to supply combustion gas to the turbine; a compressor rotatable about the rotational shaft to generate compressed air; and the compressor diffuser according to claim 1.