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A tube seal is fitted with a spherical spring, being an elastic member, at one end of a tubular barrel. The end where the spring is fitted to the tubular barrel is inserted into a steam supply pipe outlet, which is a coolant passage provided in a rotor disk. The other end of the barrel is formed int

A tube seal is fitted with a spherical spring, being an elastic member, at one end of a tubular barrel. The end where the spring is fitted to the tubular barrel is inserted into a steam supply pipe outlet, which is a coolant passage provided in a rotor disk. The other end of the barrel is formed into a spherical shape, and this end is inserted into a steam supply port in a dynamic blade, being another coolant passage port, and abuts against the internal surface of the steam supply port.

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1. A joint structure of a coolant passage in a gas turbine comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provide

1. A joint structure of a coolant passage in a gas turbine comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provided at a root of the dynamic blade; anda tube seal having a tubular barrel, an end of the barrel having a spherical shape inserted into the second coolant passage port, and a side of the barrel having an elastic member configured to deform in a radial direction of the barrel inserted into the first coolant passage port,wherein an internal surface of the second coolant passage port and the spherical end of the tubular barrel come in line contact with each other. 2. The joint structure according to claim 1, wherein the tube seal comprises a protruding portion on the side of the barrel inserted into the first coolant passage port, an outer diameter of the protruding portion being larger than that of the barrel and smaller than that of the elastic member. 3. A joint structure of a coolant passage in a gas turbine comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provided at a root of the dynamic blade, the second coolant passage port having an internal surface that is conical and that tapers towards a tip of the dynamic blade; anda tube seal having a tubular barrel, an end of the barrel having a spherical shape inserted into the second coolant passage port, and a side of the barrel having an elastic member configured to deform in a radial direction of the barrel inserted into the first coolant passage port. 4. The joint structure according to claim 3, wherein the tube seal comprises a protruding portion on the side of the barrel inserted into the first coolant passage port, an outer diameter of the protruding portion being larger than that of the barrel and smaller than that of the elastic member. 5. A joint structure of a coolant passage in a gas turbine comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provided at a root of the dynamic blade, the second coolant passage port having an internal surface that is conical and that tapers towards a tip of the dynamic blade; anda tube seal having a tubular barrel, a working face formed on an outer periphery of an end of the barrel inserted into the second coolant passage port, a side of the barrel having an elastic member configured to deform in a radial direction of the barrel inserted into the first coolant passage port, and a protruding portion provided on the side of the barrel configured to restrict a radial movement of the barrel by abutting against at least one of internal surfaces of the first and the second coolant passage ports. 6. A tube seal having a tubular barrel an end of which is formed into a spherical shape, and a side of the barrel configured to be inserted into a coolant passage port provided with an elastic member configured to deform in a radial direction of the barrel. 7. The tube seal according to claim 6, wherein the tube seal comprises a protruding portion on the side of the barrel configured to be inserted into the coolant passage port, an outer diameter of the protruding portion being larger than that of the barrel and smaller than that of the elastic member. 8. A gas turbine comprising:a compressor configured to compress air to produce combustion air;a combustor configured to supply a fuel to the combustion air produced by the compressor to generate a combustion gas; anda turbine having a joint structure of a coolant passage, the joint structure comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provided at a root of the dynamic blade; anda tube seal having a tubular barrel, an end of the barrel having a spherical shape inserted into the second coolant passage port, and a side of the barrel having an elastic member configured to deform in a radial direction of the barrel inserted into the first coolant passage port,wherein an internal surface of the second coolant passage port and the spherical end of the tubular barrel come in line contact with each other. 9. A gas turbine comprising:a compressor configured to compress air to produce combustion air;a combustor configured to supply a fuel to the combustion air produced by the compressor to generate a combustion gas; anda turbine having a joint structure of a coolant passage, the joint structure comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provided at a root of the dynamic blade, the second coolant passage port having an internal surface that is conical and that tapers towards a tip of the dynamic blade; anda tube seal having a tubular barrel, an end of the barrel having a spherical shape inserted into the second coolant passage port, and a side of the barrel having an elastic member configured to deform in a radial direction of the barrel inserted into the first coolant passage port. 10. A gas turbine comprising:a compressor configured to compress air to produce combustion air;a combustor configured to supply a fuel to the combustion air produced by the compressor to generate a combustion gas; anda turbine having a joint structure of a coolant passage, the joint structure comprising:a rotor disk having a first coolant passage port configured to supply or to recover a coolant to or from a dynamic blade, the dynamic blade being fitted to an outer periphery of the rotor disk;a second coolant passage port provided at a root of the dynamic blade, the second coolant passage port having an internal surface that is conical and that tapers towards a tip of the dynamic blade; anda tube seal having a tubular barrel, a working face formed on an outer periphery of an end of the barrel inserted into the second coolant passage port, a side of the barrel having an elastic member configured to deform in a radial direction of the barrel inserted into the first coolant passage port,and a protruding portion provided on the side of the barrel configured to restrict a radial movement of the barrel by abutting against at least one of internal surfaces of the first and the second coolant passage ports.