Patent Publication Number: US-2023160339-A1

Title: Multi-mode engine system with gas turbine engine and turbo-compressor

Description:
BACKGROUND OF THE DISCLOSURE 
     1. Technical Field 
     This disclosure relates generally to an engine system and, more particularly, to an engine system with a gas turbine engine. 
     2. Background Information 
     A gas turbine engine is typically configured for generating thrust and/or power. During operation, the gas turbine engine requires an energy input by way of combusting/burning fuel. By contrast, a turbo-compressor utilizes energy from one gas flow input to compress another gas flow input without requiring an additional energy input. Gas turbine engines and turbo-compressors may be used, but are discrete, in modern engine systems. While these modern engine systems have various benefits, there is still room in the art for improvement. 
     SUMMARY OF THE DISCLOSURE 
     According to an aspect of the present disclosure, an engine system is provided that includes a compressor section, a combustor section, a turbine section, a flowpath and a flow regulator. The combustor section includes a combustion chamber. The flowpath extends sequentially through the compressor section, the combustor section and the turbine section. The flow regulator is configured to open the flowpath between the compressor section and the combustion chamber during a first mode of operation. The flow regulator is configured to at least substantially close the flowpath between the compressor section and the combustion chamber during a second mode of operation. 
     According to another aspect of the present disclosure, another engine system is provided that includes a compressor section, a combustor section, a turbine section, a gas turbine engine and a turbo-compressor. The compressor section includes a compressor rotor. The turbine section includes a turbine rotor. The gas turbine engine includes the compressor section, the combustor section and the turbine section during a first mode of operation. The combustor section is fluidly coupled with and between the compressor section and the turbine section during the first mode of operation. The turbo-compressor includes the compressor rotor and the turbine rotor during a second mode of operation. The turbine section is fluidly decoupled from the compressor section during the second mode of operation. 
     According to still another aspect of the present disclosure, a method is provided for operating an engine system. During this method, compressed gas is directed from a compressor section to a combustor section. Fuel mixed with the compressed gas is ignited within the combustor section to provide combustion products. The combustion products are directed through a turbine section to drive the compressor section. The compressor section is fluidly decoupled from the turbine section. The compressed gas is directed from the compressor section to a fluid receiver. Second gas is directed from a fluid source into the turbine section to drive a compressor rotor in the compressor section. 
     The engine system may also include a flow regulator configured to fluidly couple the compressor section with a combustion chamber within the combustor section during the first mode of operation. The flow regulator may be configured to fluidly decouple the compressor section from the combustion chamber during the second mode of operation. 
     The compressor section, the combustor section and the turbine section may be configured as a gas turbine engine during the first mode of operation. 
     During the first mode of operation, the combustor section is configured to: receive compressed gas from the compressor section; ignite a mixture of the compressed gas and fuel within the combustion chamber to provide combustion products; and direct the combustion products into the turbine section. 
     The compressor section and the turbine section may be configured as a turbo-compressor during the second mode of operation. 
     The combustor section may be operational during the first mode of operation. 
     The combustor section may be non-operational during the second mode of operation. 
     The compressor section may include a compressor rotor. The turbine section may include a turbine rotor. The turbine rotor may be mechanically coupled to the compressor rotor by a shaft. 
     The engine system may also include a fluid receiver and a fluid source. The fluid receiver may be configured to receive first gas from the compressor section during the second mode of operation. The fluid source may be configured to direct second gas into the turbine section during the second mode of operation. 
     The fluid receiver may be configured to receive the first gas from the compressor section during the first mode of operation. 
     The fluid source may be configured to direct the second gas into the turbine section during the first mode of operation. 
     The fluid receiver may be configured as or otherwise include a heat exchanger. 
     The engine system may also include a gas turbine engine which includes the fluid receiver. The gas turbine engine may be discrete from the compressor section, the combustor section and the turbine section. 
     The fluid receiver may be configured as or otherwise include a reservoir. 
     The fluid source may be configured as or otherwise include a reservoir. 
     The fluid source may be configured as or otherwise include a ram air intake. 
     The engine system may also include a gas turbine engine which includes the fluid source. The gas turbine engine may be discrete from the compressor section, the combustor section and the turbine section. 
     The compressor section may be configured as or otherwise include an axial flow compressor section. In addition or alternatively, the turbine section may be configured as or otherwise include an axial flow turbine section. 
     The compressor section may be configured as or otherwise include a radial flow compressor section. In addition or alternatively, the turbine section may be configured as or otherwise include a radial flow turbine section. 
     The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof. 
     The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is a schematic illustration of a multi-mode engine system configured with an axial flow compressor section and an axial flow turbine section. 
         FIG.  2    is a schematic illustration of the engine system of  FIG.  1    during a gas turbine engine mode of operation. 
         FIG.  3    is a schematic illustration of the engine system of  FIG.  1    during a turbo-compressor mode of operation. 
         FIG.  4    is a schematic illustration of the engine system configured with a radial flow compressor section and a radial flow turbine section. 
         FIG.  5    is a schematic illustration of the engine system of  FIG.  4    during a gas turbine engine mode of operation. 
         FIG.  6    is a schematic illustration of the engine system of  FIG.  4    during a turbo-compressor mode of operation. 
         FIGS.  7 A and  7 B  are illustrations of a flow regulator arranged with a flowpath. 
         FIGS.  8 A and  8 B  are illustrations of another flow regulator. 
         FIGS.  9 A- 9 C  are schematic illustrations of various flow regulator actuation configurations. 
         FIG.  10    is a schematic illustration of a fluid source assembly for the engine system. 
     
    
    
     DETAILED DESCRIPTION 
       FIG.  1    illustrates a multi-mode engine system  20 . This engine system  20  is configured with a gas turbine engine  22  during a gas turbine engine mode of operation; e.g., see  FIG.  2   . The engine system  20  is configured with a turbo-compressor  24  during a turbo-compressor mode of operation; e.g., see  FIG.  3   . 
     The engine system  20  of  FIG.  1    includes an engine inlet  26 , a compressor section  28 , a combustor section  30 , a turbine section  32 , an engine exhaust  34  and a (e.g., annular) core flowpath  36  extending sequentially from the engine inlet  26 , through the compressor section  28 , the combustor section  30  and the turbine section  32 , to the engine exhaust  34 . This engine system  20  also includes a fluid source  38 , a fluid receiver  40  and a flow regulator  42 . 
     The compressor section  28  includes a compressor rotor  44  configured to rotate about a rotational axis  46  of the gas turbine engine  22 /the turbo-compressor  24 . This compressor rotor  44  includes a plurality of compressor rotor blades arranged circumferentially around and connected to one or more respective compressor rotor disks. The compressor rotor blades are disposed within the core flowpath  36 . Each compressor rotor disk is rotatable about the rotational axis  46 . 
     The compressor section  28  may be configured as an axial flow compressor section. The core flowpath  36  of  FIG.  1   , for example, extends axially along the rotational axis  46  into, within and out of the compressor section  28 . The compressor section  28  may alternatively be configured as a radial flow compressor section. The core flowpath  36  of  FIG.  4   , for example, extends axially along the rotational axis  46  into the compressor section  28 . The core flowpath  36  turns radially outward within the compressor section  28 . The core flowpath  36  extends radially outwards relative to the rotational axis  46  out of the compressor section  28 . 
     The combustor section  30  of  FIG.  1    is fluidly coupled between the compressor section  28  and the turbine section  32 . The combustor section  30  includes at least one combustor  48  with an internal combustion chamber  50 . The combustor  48  may be configured as an annular combustor which extends circumferentially around the rotational axis  46 . The combustor  48  may alternatively be configured as a (e.g., non-annular) CAN-type combustor. In such embodiments, the combustor  48  may be one of a plurality of combustors  48  within the combustor section  30 , and the combustors  48  may be distributed circumferentially about the rotational axis  46 . 
     The turbine section  32  includes a turbine rotor  52  configured to rotate about the rotational axis  46 . This turbine rotor  52  includes a plurality of turbine rotor blades arranged circumferentially around and connected to one or more respective turbine rotor disks. The turbine rotor blades are disposed within the core flowpath  36 . Each turbine rotor disk is rotatable about the rotational axis  46 . The turbine rotor  52  of  FIG.  1    is mechanically coupled to the compressor rotor  44  through an engine shaft  54 . 
     The turbine section  32  may be configured as an axial flow turbine section. The core flowpath  36  of  FIG.  1   , for example, extends axially along the rotational axis  46  into, within and out of the turbine section  32 . The turbine section  32  may alternatively be configured as a radial flow turbine section. The core flowpath  36  of  FIG.  4   , for example, extends radially inward relative to the rotational axis  46  into the turbine section  32 . The core flowpath  36  turns axially along the rotational axis  46  within the turbine section  32 . The core flowpath  36  extends axially along the rotational axis  46  out of the turbine section  32 . 
     The fluid source  38  is configured to provide fluid source gas to the combustor section  30  and its combustor  48 . This fluid source gas may be compressed gas and/or high velocity gas. The fluid source  38 , for example, may be configured as a reservoir such as a bottle, a tank, a cylinder, a bladder or any other type of pressure vessel. The reservoir, for example, may be configured as an oxygen ( 02 ) bottle. The fluid source  38  may alternatively be configured as (or also include) an intake, which may be discrete from the engine inlet  26 . The intake, for example, may be configured as a ram air intake or any other type of forced induction intake. The fluid source  38  may still alternatively be configured as (or also include) an internal combustion (IC) engine which is discrete from the gas turbine engine  22 . This IC engine may be a gas turbine engine, and the fluid source gas may be compressed air bled from a compressor section of that gas turbine engine and/or exhaust gas bled or otherwise received from an exhaust of that gas turbine engine. The present disclosure, however, is not limited to the foregoing exemplary fluid source types/configurations. 
     The fluid receiver  40  is configured to receive compressed gas bled or otherwise received from the compressor section  28 . The fluid receiver  40 , for example, may be configured as a component of a heat exchanger system; e.g., a heat exchanger. The fluid receiver  40  may alternatively be configured as (or also include) a reservoir for containing/storing the compressed gas for later use. The fluid receiver  40  may still alternatively be configured as (or also include) an internal combustion (IC) engine which is discrete from the gas turbine engine  22 . This IC engine may be a gas turbine engine (e.g., a main propulsion system engine), where the compressed gas received from the compressor section  28  may be utilized during, for example, startup of that gas turbine engine. 
     The flow regulator  42  is configured to regulate gas (e.g., air) flow through the core flowpath  36  downstream of the compressor section  28 /the compressor rotor  44 . The flow regulator  42  of  FIG.  1   , for example, is configured to regulate the gas flow directed through the core flowpath  36  from the compressor section  28  to the combustor  48  and its combustion chamber  50 . For example, during the gas turbine engine mode of operation of  FIG.  2    (see also  FIG.  5   ), the flow regulator  42  may open (e.g., facilitate flow through) a portion  56  of the core flowpath  36  between the compressor rotor  44  and the combustion chamber  50 . The flow regulator  42  may thereby fluidly couple the compressor section  28  with the combustor section  30  and its combustion chamber  50 . However, during the turbo-compressor mode of operation of  FIG.  3    (see also  FIG.  6   ), the flow regulator  42  may substantially or completely close (e.g., cutoff flow through) the portion  56  of the core flowpath  36  between the compressor rotor  44  and the combustion chamber  50 , where the flow regulator  42  may substantially close the portion  56  of the core flowpath  36  by reducing flow therethrough at least, for example, eighty or ninety percent (80-90%). The flow regulator  42  may thereby fluidly decouple the compressor section  28  from the combustor section  30  and its combustion chamber  50 . 
     Referring to  FIGS.  7 A and  7 B , the flow regulator  42  may configured as or otherwise include a pivot member  58 ; e.g., mechanical flap, a door, etc. This pivot member  58  is disposed within the core flowpath  36 , and is pivotable about a pivot axis between an open position (see  FIG.  7 A ) and a closed position (see  FIG.  7 B ). In the open position of  FIG.  7 A , the pivot member  58  may be positioned against a flowpath wall  60  to a side of the core flowpath  36  to facilitate the flow of gas (e.g., compressed air) through the flow regulator  42  and the core flowpath portion  56  during the gas turbine engine mode of operation. In the closed position of  FIG.  7 B , the pivot member  58  may extend across and substantially or completely block the core flowpath  36  to cut off the flow of gas (e.g., compressed air) through the flow regulator  42  and the core flowpath portion  56  during the turbo-compressor mode of operation. 
     Referring to  FIGS.  8 A and  8 B , the flow regulator  42  may alternatively be configured as or otherwise include a rotatable member  62 ; e.g., a rotating cylinder. This rotatable member  62  is disposed within the core flowpath  36  (see  FIGS.  1  and  4   ), and is rotatable about an axis (e.g., the rotational axis  46 ) between an open position (see  FIG.  8 A ) and a closed position (see  FIG.  8 B ). In the open position of  FIG.  8 A , one or more ports  64  in the rotatable member  62  may be respectively aligned with one or more ports  66  in an adjacent (e.g., stationary) member  68  to facilitate the flow of gas (e.g., compressed air) through the flow regulator  42  and the core flowpath portion  56  (see  FIGS.  2  and  5   ) during the gas turbine engine mode of operation. In the closed position of  FIG.  8 B , the ports  64  in the rotatable member  62  may be offset from the ports  66  in the adjacent member  68  and the rotatable member  62  may block the ports  66  in the adjacent member  68  to cut off the flow of gas (e.g., compressed air) through the flow regulator  42  and the core flowpath portion  56  (see  FIGS.  3  and  6   ) during the turbo-compressor mode of operation. 
       FIGS.  7 A- 8 B  illustrate various exemplary embodiments of the flow regulator  42 . The present disclosure, however, is not limited to such exemplary flow regulator types/configurations. The flow regulator  42 , for example, may alternatively be configured as or otherwise include various types of valves. Furthermore, while the flow regulator  42  is described above as moving between a (e.g., fully) open position and a (e.g., fully) closed position, it is contemplated the flow regulator  42  may also move to one or more intermediate positions during the gas turbine engine mode of operation, the turbo-compressor mode of operation and/or another mode of operation to reduce, but not cutoff, gas flow through the flow regulator  42 /the core flowpath portion  56  to the combustion chamber  50 . 
     Referring to  FIG.  9 A , the flow regulator  42  and its moveable member  58 ,  62  (see also  FIGS.  7 A- 8 B ) may be hydraulically actuated. The flow regulator  42  of  FIG.  9 A , for example, includes a hydraulic actuator  70  (e.g., a hydraulic cylinder) configured to move the moveable member  58 ,  62  between its open position (e.g., see  FIGS.  7 A and  8 A ) and its closed position (e.g., see  FIGS.  7 B and  8 B ). This hydraulic actuator  70  may be fluidly coupled to a hydraulic fluid source  72  (e.g., a pump, etc.) through a control valve  74 . 
     Referring to  FIG.  9 B , the flow regulator  42  and its moveable member  58 ,  62  (see also  FIGS.  7 A- 8 B ) may alternatively be pneumatically actuated. The flow regulator  42  of  FIG.  9 B , for example, includes a pneumatic actuator  76  configured to move the moveable member  58 ,  62  between its open position (e.g., see  FIGS.  7 A and  8 A ) and its closed position (e.g., see  FIGS.  7 B and  8 B ). This pneumatic actuator  76  may be fluidly coupled to a pneumatic fluid source  78  (e.g., a compressor, a pressure vessel, etc.) through a control valve  80 . The pneumatic fluid source  78  may also be the fluid source  38 , or discrete from the fluid source  38 . 
     Referring to  FIG.  9 C , the flow regulator  42  and its moveable member  58 ,  62  (see also  FIGS.  7 A- 8 B ) may alternatively be electrically actuated. The flow regulator  42  of  FIG.  9 C , for example, includes an electric actuator  82  (e.g., an electric step motor) configured to move the moveable member  58 ,  62  between its open position (e.g., see  FIGS.  7 A and  8 A ) and its closed position (e.g., see  FIGS.  7 B and  8 B ). 
     Referring to  FIG.  1   , the engine system  20  may include one or more additional flow regulators  84  and  86 . The fluid source flow regulator  84  (e.g., at least one valve) is configured to regulate the flow of the fluid source gas from the fluid source  38  to one or more outlets  88  (e.g., injectors) (one visible in  FIG.  1   ). These outlets  88  of  FIG.  1    are configured to direct (e.g., inject) the fluid source gas into the combustor  48  and its the combustion chamber  50  during the gas turbine engine mode of operation, the turbo-compressor mode of operation and/or another mode of operation. In some embodiments, referring to  FIG.  10   , the fluid source flow regulator  84  may also be configured to select which one or more fluid sources  38  (when multiple are available) to fluidly couple to the outlets  88 . 
     Referring again to  FIG.  1   , the fluid receiver flow regulator  86  (e.g., at least one valve) is configured to regulate the flow of the compressed gas from one or more inlets  90  (e.g., bleed ports) (one visible in  FIG.  1   ) to the fluid receiver  40 . These inlets  90  are configured to receive (e.g., bleed and/or redirect) the compressed gas from the compressor section  28  during the gas turbine engine mode of operation, the turbo-compressor mode of operation and/or another mode of operation. 
     During the gas turbine engine mode of operation of  FIG.  2    (see also  FIG.  5   ), gas (e.g., air) is directed into the core flowpath  36  through the engine inlet  26 . This gas is compressed within the compressor section  28  by the compressor rotor  44  and directed through the flow regulator  42  into the combustor section  30  and its combustion chamber  50 . Fuel is injected into the combustion chamber  50  via one or more fuel injectors  92  (see  FIGS.  1  and  4   ), where the fuel is mixed with the compressed gas to provide a gas-fuel mixture. This gas-fuel mixture is ignited within the combustion chamber  50  by one or more igniters to provide combustion products. These combustion products are directed into the turbine section  32  and cause the turbine rotor  52  to rotate. The rotation of the turbine rotor  52  drives rotation of the compressor rotor  44 . The combustion products are subsequently exhausted from the gas turbine engine  22  through the engine exhaust  34 . These exhausted combustion products may provide engine thrust where, for example, the gas turbine engine  22  is configured as part of a propulsion system for an aircraft. The exhausted combustion products may alternatively be diffused where, for example, the gas turbine engine  22  is configured as part of a power generation system; e.g., an electrical power generator, a hydraulic power system, etc. 
     During the turbo-compressor mode of operation of  FIG.  3    (see also  FIG.  6   ), the fuel flow to the fuel injectors  92  (see  FIGS.  1  and  4   ) is turned off. The flow regulator  42  is also (subsequently, or simultaneously) moved to its closed position to cutoff the flow of the compressed gas from the compressor section  28  to the combustor  48  and its combustion chamber  50 . The turbine rotor  52  is thereby no longer rotated by combustion products form the combustion chamber  50 . However, the fluid source gas from the fluid source  38  is directed into the flowpath downstream of the closed flow regulator  42  (e.g., within the combustion chamber  50 ), which fluid source gas flows through the turbine section  32  causing the turbine rotor  52  to rotate. The rotation of the of the turbine rotor  52  drives rotation of the compressor rotor  44 . The rotation of the compressor rotor  44  compresses the gas received from the engine inlet  26  to provide the compressed gas. This compressed gas is directed out of the compressor section  28  and the core flowpath  36 , upstream of the closed flow regulator  42 , to the fluid receiver  40 . The turbo-compressor  24  is thereby operable to provide (or maintain) the flow of the compressed gas to the fluid receiver  40  even where the combustor section  30  and, thus, the gas turbine engine  22  are non-operational. This may reduce fuel consumption of the engine system  20 . During the turbo-compressor mode of operation, the flow of the compressed gas provided to the fluid receiver  40  may be directly regulated by adjusting (e.g., metering flow through) the fluid receiver flow regulator  86 , and/or indirectly regulated by adjusting (e.g., metering flow through) the fluid source flow regulator  84 . 
     In some embodiments, the compressed gas may also be bled from the compressor section  28  and directed to the fluid receiver  40  during the gas turbine engine mode of operation. The fluid source gas may also or alternatively be provided to the combustor section  30  (e.g., directed into the combustion chamber  50 ) during the gas turbine engine mode of operation. The provision of this fluid source gas may aid in, for example, high altitude startup of the combustor section  30 . 
     In some embodiments, referring to  FIGS.  1  and  4   , the engine system  20  may include one or more accessories  94  (e.g., shaft mounted accessories) driven by a rotating assembly  96 , which rotating assembly  96  may include the compressor rotor  44 , the turbine rotor  52  and the engine shaft  54 . Examples of the accessories  94  include, but are not limited to, a pump and an electrical generator. Alternatively, the rotating assembly  96  may mechanically drive another apparatus discrete from the gas turbine engine  22 . 
     The gas turbine engine  22  may have various configurations other than the those shown in  FIGS.  1 - 6   . The gas turbine engine  22 , for example, may be configured as a geared turbine engine where a gear train connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section. Alternatively, the gas turbine engine  22  may be as a direct drive turbine engine configured without a gear train. The gas turbine engine  22  may be configured with a single spool (see  FIGS.  1 - 6   ), with two spools, or with more than two spools. The gas turbine engine  22  may be configured as a turbofan engine, a turbojet engine, a turboprop engine, a turboshaft engine, a propfan engine, a pusher fan engine or any other type of turbine engine. The gas turbine engine  22  may alternatively be configured as an auxiliary power unit (APU) or an industrial gas turbine engine. 
     While various embodiments of the present disclosure have been described, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.