阅读说明：本技术 涡轮机匣、涡轮及航空发动机 (Turbine casing, turbine and aeroengine ) 是由 甘明瑜 胡颂军 李天雄 曾飞 郭艳龙 于 2020-07-21 设计创作，主要内容包括：本公开涉及航空技术领域,尤其涉及一种涡轮机匣、涡轮及航空发动机。该涡轮机匣能够利用冷气对叶尖间隙进行调整,该叶尖间隙为涡轮机匣和涡轮转子之间的间隙,该涡轮机匣包括外匣、冷却环、引气管路和涡轮环,其中：外匣包括匣体部、第一突出部和第二突出部；冷却环上设有冷却孔,并与匣体部、第一突出部和第二突出部围成空腔；引气管路连通于空腔；涡轮环包括垂直设置的第一环部和第二环部,第二环部连接于第二突出部,第一环部和冷却环分开设置,第一环部和涡轮转子之间的间隙为叶尖间隙。由此,冷气能够经引气管路、空腔和冷却孔吹到涡轮环,并对涡轮转子进行降温,从而实现叶尖间隙的调整,且结构较为简单,使得涡轮机匣的成本也较低。(The disclosure relates to the technical field of aviation, in particular to a turbine casing, a turbine and an aircraft engine. This turbine casing can utilize the air conditioning to adjust the apex clearance, and this apex clearance is the clearance between turbine casing and the turbine rotor, and this turbine casing includes outer casket, cooling ring, bleed air line and turbine ring, wherein: the outer cartridge includes a cartridge body portion, a first projection, and a second projection; the cooling ring is provided with a cooling hole and forms a cavity with the box body part, the first protruding part and the second protruding part in an enclosing way; the air-entraining pipeline is communicated with the cavity; the turbine ring comprises a first ring portion and a second ring portion which are vertically arranged, the second ring portion is connected to the second protruding portion, the first ring portion and the cooling ring are separately arranged, and a gap between the first ring portion and the turbine rotor is a blade tip gap. From this, air conditioning can blow to the turbine ring through bleed air pipeline, cavity and cooling hole to cool down the turbine rotor, thereby realize the adjustment of apex clearance, and the structure is comparatively simple, makes the cost of turbine casket also lower.)

1. A turbine case capable of adjusting a tip clearance, which is a clearance between the turbine case and a turbine rotor installed in the turbine case, using cool air, the turbine case comprising:

the outer box comprises a box body part, a first protruding part and a second protruding part, and the first protruding part and the second protruding part are arranged on one side, close to the turbine rotor, of the box body part;

the cooling ring is arranged on one side, close to the turbine rotor, of the outer box and surrounds a cavity with the box body part, the first protruding part and the second protruding part; the cooling ring is provided with a cooling hole;

the bleed pipeline is arranged on one side, far away from the turbine rotor, of the casing and is communicated with the cavity;

the turbine ring comprises a first ring part and a second ring part which are vertically arranged, the second ring part is connected to one side, away from the first protruding part, of the second protruding part, the first ring part and the cooling ring are separately arranged, and a gap between the first ring part and the turbine rotor is the blade tip gap;

the cold air can be blown to the first ring part through the air guide pipeline, the cavity and the cooling hole, and the turbine rotor is cooled, so that the blade tip clearance is adjusted.

2. The turbine case of claim 1, wherein the cooling ring comprises a first end portion, an intermediate portion, and a second end portion; the first end portion is connected to the first protruding portion, the second end portion is connected to the second protruding portion, and the middle portion is provided with a cooling hole.

3. The turbine case of claim 2, wherein the second end portion is perpendicular to the middle portion and the first end portion, the second end portion being connected between the second protrusion and the second ring portion.

4. The turbine case of claim 3, further comprising:

a connector disposed through the second protrusion, the second end, and the second ring portion for connecting the outer casing, the cooling ring, and the turbine ring.

5. The turbine case according to claim 3, wherein the number of the cooling holes is plural, and the plural cooling holes are evenly distributed on the intermediate portion.

6. The turbine case of claim 5, wherein the cooling holes are positioned directly opposite the turbine rotor.

7. The turbine casing of claim 3, wherein a gap is left between the first ring portion and the first end portion, and wherein the cold air can be blown from the turbine ring to the turbine rotor through the gap.

8. A turbine mountable in an aircraft engine, the turbine comprising:

the turbine case of any one of claims 1 to 7;

a turbine rotor mounted in the turbine case, a gap between the turbine rotor and the turbine case being the tip gap;

the guider is connected to the turbine casing, is opposite to the turbine rotor, and is used for guiding the combustion gas of the aircraft engine to the turbine rotor, and the turbine rotor rotates under the impact of the combustion gas.

9. The turbine of claim 8, wherein the aircraft engine comprises an exhaust frame;

the exhaust frame is connected to one end, far away from the guider, of the turbine casing, and gas impacting the turbine rotor to rotate is exhausted through the exhaust frame.

10. An aircraft engine comprising a turbine as claimed in any one of claims 8 to 9.