# US 2021/0277832 A1 · Rotational support for an interdigitated rotor assembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0277832 A1 - Document ID: US20210277832A1 - Status: Published application - Kind: A1 - Application number: 17/178,371 - Filed: 2021-02-18 - Published: 2021-09-09 - Earliest claimed: 2020-03-06 - Assignees: GE Avio S.r.l. - Applicants: GE Avio S.r.l. - Inventors: Roberto Maddaleno; Matteo Renato Usseglio; Darek Tomasz Zatorski - Web page: https://patentgrep.com/patent/US20210277832A1 ## 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) - F01D 25/162: {Bearing supports} - F02C 3/067: having counter-rotating rotors (F02C3/073 takes precedence) - F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/50: Bearings - F05D 2240/54: Radial bearings - F05D 2240/60: Shafts - F05D 2260/40: Transmission of power - 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) - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Turbomachines and turbine sections of a turbomachine are provided. For example, a turbomachine comprises a turbine section having a turbine comprising a first plurality and a second plurality of turbine rotor blades, which are alternatingly spaced along an axial direction. At least one turbine blade of the first plurality of turbine blades is attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades is attached to a second support member assembly. The turbomachine further comprises a spool that connects the turbine with one or more components outside the turbine section, a first rotational support, and a gearbox. Both the first support member assembly and the second support member assembly are attached to the first rotational support and coupled to the gearbox such that the first and second pluralities of turbine rotor blades are rotatable with one another through the gearbox. ## Claims ### Claim 1 A turbomachine defining a radial direction and an axial direction, the turbomachine comprising: a turbine section comprising a turbine, the turbine comprising a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction, at least one turbine blade of the first plurality of turbine blades attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades attached to a second support member assembly; a spool that connects the turbine with one or more components outside the turbine section; a first rotational support, both the first support member assembly and the second support member assembly attached to the first rotational support; and a gearbox, both the first support member assembly and the second support member assembly coupled to the gearbox such that the first plurality of turbine rotor blades and second plurality of turbine rotor blades are rotatable with one another through the gearbox. ### Claim 2 (depends on 1) The turbomachine of claim 1, further comprising: a turbine center frame having an inner center frame support member and an outer center frame support member, wherein the inner center frame support member is disposed between the first rotational support and the spool. ### Claim 3 (depends on 2) The turbomachine of claim 2, further comprising: a second rotational support, wherein both the outer center frame support member and the second support member assembly are attached to the second rotational support. ### Claim 4 (depends on 2) The turbomachine of claim 2, further comprising: a third rotational support, wherein both the inner center frame support member and the spool are attached to the third rotational support. ### Claim 5 (depends on 1) The turbomachine of claim 1, further comprising: a second rotational support, wherein both the first support member assembly and the second support member assembly are attached to the second rotational support. ### Claim 6 (depends on 1) The turbomachine of claim 1, further comprising: a turbine rear frame having a rear frame support member; and a third rotational support, wherein both the rear frame support member and the first support member assembly are attached to the third rotational support. ### Claim 7 (depends on 1) The turbomachine of claim 1, wherein the first rotational support is a ball bearing. ### Claim 8 (depends on 1) The turbomachine of claim 1, wherein the first support member assembly is connected to the spool such that the gearbox is positioned between the first rotational support and the spool. ### Claim 9 (depends on 1) The turbomachine of claim 1, wherein the turbine is a low pressure turbine, and wherein the spool is a low speed spool drivingly connected to a low pressure compressor of a compressor section disposed forward of the turbine section. ### Claim 10 (depends on 1) The turbomachine of claim 1, wherein the first rotational support is disposed forward of the gearbox. ### Claim 11 (depends on 1) The turbomachine of claim 1, wherein the first rotational support and the gearbox are disposed in a common sump. ### Claim 12 (depends on 1) The turbomachine of claim 1, further comprising: a scavenge for servicing both the first rotational support and the gearbox such that the scavenge is common to both the first rotational support and the gearbox. ### Claim 13 (depends on 1) The turbomachine of claim 1, further comprising: a thermal barrier for thermally shielding both the first rotational support and the gearbox such that the thermal barrier is common to both the first rotational support and the gearbox. ### Claim 14 (depends on 1) The turbomachine of claim 1, wherein at least one turbine rotor blade of the first or second pluralities of turbine rotor blades is axially aligned with a portion of the first rotational support. ### Claim 15 (depends on 1) The turbomachine of claim 1, wherein the first plurality of turbine rotor blades are configured to rotate in a first circumferential direction and the second plurality of turbine rotor blades are configured to rotate in a second circumferential direction, and wherein the second circumferential direction is opposite the first circumferential direction. ### Claim 16 A turbine section of a turbomachine, the turbine section comprising: a turbine, the turbine comprising a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction, at least one turbine blade of the first plurality of turbine blades attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades attached to a second support member assembly; a first rotational support, both the first support member assembly and the second support member assembly attached to the first rotational support; a gearbox, both the first support member assembly and the second support member assembly coupled to the gearbox such that the first plurality of turbine rotor blades and second plurality of turbine rotor blades are rotatable with one another through the gearbox; and a turbine center frame having an inner center frame support member extending axially aft from a forward end of the turbine section to the gearbox, wherein the first support member assembly is connected to a spool, and wherein the inner center frame support member is disposed between the first rotational support and the spool. ### Claim 17 (depends on 16) The turbine section of claim 16, wherein the first support member assembly is connected to the spool such that the gearbox is positioned between the first rotational support and the spool. ### Claim 18 (depends on 17) The turbine section of claim 17, further comprising: a second rotational support; and a third rotational support, wherein both an outer center frame support member of the turbine center frame and the second support member assembly are attached to the second rotational support, and wherein both the inner center frame support member and the spool are attached to the third rotational support. ### Claim 19 (depends on 16) The turbine section of claim 16, further comprising: a sump, both the first rotational support and the gearbox disposed in the sump such that the sump is common to both the first rotational support and the gearbox; a scavenge for servicing both the first rotational support and the gearbox such that the scavenge is common to both the first rotational support and the gearbox; and a thermal barrier for thermally shielding both the first rotational support and the gearbox such that the thermal barrier is common to both the first rotational support and the gearbox. ### Claim 20 A turbine section of a turbomachine, the turbine section comprising: a low pressure turbine, the low pressure turbine comprising a first plurality of turbine rotor blades and a second plurality of turbine rotor blades, the first plurality of turbine rotor blades and second plurality of turbine rotor blades alternatingly spaced along the axial direction, at least one turbine blade of the first plurality of turbine blades attached to a first support member assembly and at least one turbine blade of the second plurality of turbine blades attached to a second support member assembly; a ball bearing, each of the first support member assembly and the second support member assembly attached to the ball bearing; a gearbox, each of the first support member assembly and the second support member assembly coupled to the gearbox such that the first plurality of turbine rotor blades and second plurality of turbine rotor blades are rotatable with one another through the gearbox; and a turbine center frame having an inner center frame support member extending axially from a forward end of the turbine section aft to the gearbox, wherein the first plurality of turbine rotor blades are configured to rotate in a first circumferential direction and the second plurality of turbine rotor blades are configured to rotate in a second circumferential direction, the second circumferential direction opposite the first circumferential direction, wherein the first support member assembly is connected to a low speed spool, the low speed spool drivingly connected to a low pressure compressor disposed forward of the turbine section, and wherein the inner center frame support member is disposed between the ball bearing and the low speed spool.